830 Sentences With "perigee" | Random Sentence Generator

And when this particular celestial alignment also happens to coincide with perigee, we get an exceptionally close full moon, also known as a perigee moon or a supermoon.

In the UK, perigee will occur at 11:23 a.m. GMT.

In its closest point, or perigee, it's around 222,000 miles away.

A supermoon occurs when the moon's orbit is closest (perigee) to Earth.

But even among the elite perigee moons, there's some variation in size.

The moon will reach fullness just three hours after perigee on November 14.

A supermoon occurs when the moonâ€™s orbit is closest (perigee) to Earth.

The moon will reach perigee within two hours of becoming full, according to NASA.

Sometimes, a full moon aligns with perigee and look a tad bigger than usual.

Supermoons occur is when the moon is at perigee — its closest point to Earth.

The first two full moons of 2018 will occur near the perigee, making them super as well.

Full moons tend to intensify tides, and have an even greater impact when the moon is at perigee.

But it has come to mean a moon that is full when it is closest to Earth — at perigee.

A supermoon is when these two cycles match up, and we have a full moon that's near its perigee.

A supermoon is when these two cycles match up and we have a full moon that's near its perigee.

Full moons occur near perigee approximately every 13 months, so supermoons like this are not that uncommon, according to NASA.

The eclipse also marked a supermoon — a full moon that is at perigee, or much closer to Earth than usual.

For example, on Monday during perigee, the moon will be approximately 222,040 miles away from our planet, in contrast to Jan.

A full moon at perigee can appear up to 14 percent larger and 30 percent brighter than a full moon at apogee.

Altitude: 22018,21 km perigee, Rotation speed has increased, now 13,21°/s -> 22:22016 min per one turn #reentry #radar #Tiangong #spacedebris pic.twitter.

Whenever the full moon phase coincides with the Moon's closest approach to Earth — known as perigee — that's when we call it super.

October's full moon did fall when the moon was closer to Earth than average, reaching full phase within a day of perigee.

A supermoon, as it's known, is when a full moon is at its perigee — the closest point to Earth along its orbit.

Altitude: 21,23 km perigee, Rotation speed has increased, now 22,22016°/s -> 22020:23 min per one turn #reentry #radar #Tiangong #spacedebris pic.twitter.

A regular moon becomes a supermoon when it reaches its perigee — the point along its orbit that is closest to the earth.

This means that it's a full moon that coincides with the moon's perigee, the point in its orbit when it's closest to Earth.

As the moon swings between its closest point (perigee) and its furthest point (apogee), its distance to Earth varies by approximately 214,000 miles.

Image: Jeff WallaceSize comparison between the moon on November 13th, 95% illuminated, and the full moon on November 14th as it approached perigee.

This is 2017's first supermoon, which means la luna is sitting at her closest proximity (or perigee in astrospeak) to planet Earth.

That's because the sun and moon—being moving objects in space rather than circles on a diagram—very rarely line up exactly at perigee.

At perigee, the closest spot in its orbit to Earth, it's around 31,068 miles closer to Earth than at apogee, when it's farthest away.

The point at which the moon is farthest from the Earth is the apogee, and the moment at which it is closest is the perigee.

Suffice it to say that on November 14th at 11:23 UTC (7:43am ET) the moon will hit perigee, its closest point to Earth.

The blue moon also will be a super moon, which occurs when it is at or near its closest point to the earth, or perigee.

At perigee, the closest spot in its orbit to the Earth, it's around 22017,068 miles closer to Earth than at apogee, when it's farthest away.

Because perigee and the full moon are so closely timed, this full moon will be the largest (relative to our perspective on Earth) since 1948.

At perigee, the closest spot in its orbit to the Earth, it's around 31,068 miles closer to Earth than at apogee, when it's farthest away.

Finally, a supermoon occurs when the full moon is at the closest point of its orbit to the Earth, which is also called the perigee.

The supermoon phenomenon occurs when the moon becomes full the same day it reaches its perigee, the point in its elliptical orbit closest to Earth.

Called the "Beaver Moon," this full phase will coincide even more closely with the Moon's perigee, making it an "extra-supermoon," according to this NASA video.

Not only will the Moon be full on Sunday evening, it will also reach perigee, or its tightest approach to Earth, at 22016:36 PM Eastern time.

Photo: AP"Now that [its] perigee is below 300 kilometers [186 miles] and it is in denser atmosphere, the rate of decay is getting higher," McDowell said.

"For this year's final supermoon, the perigee distance will be approximately 222,135 miles in the early morning hours of December 4 (in the United States)," says Nichols.

A small shadow zone Interestingly, the moon will also be very close to Earth during these celestial events; lunar perigee occurs just over 5 hours after new moon.

Sky and Telescope reports that the night of the 143th or 14th should make for good viewing (perigee will occur at 6:23 am EST on the 14th).

The term has come to loosely mean a full moon that is at perigee, or when the moon is at its closest position to Earth along its orbit.

A supermoon occurs when the moon becomes full on the same days as its perigee, which is the point in the moon's orbit when it is closest to Earth.

The elliptical orbit means the moon is 30,000 miles closer to Earth while on the shorter side of the oval-shaped orbit (the shorter side is called the perigee).

The moon will appear larger than average because it will be three days past perigee, the point in its orbit when it is nearest to Earth, according to Space.com.

Funding partners for Think Babies include the Robert Wood Johnson Foundation, which supports the campaign's public education, and the Perigee Fund, which supports the campaign's public education and advocacy.

The moon will be at its full phase as the natural satellite reaches its closest point to Earth in its orbit (called perigee), making it a supermoon on November 14.

The phenomenon "supermoon" occurs when the moon becomes full on the same day it reaches its perigee, the point in the moon's elliptical orbit when it is closest to Earth.

So let's break it down: The term "supermoon" has come to loosely mean a full moon near perigee, or the point when it is closest to Earth in its elliptical orbit.

When the moon is at apogee, compared to when it's at perigee—and where it is at both points—you're talking about a maximum perceived difference in diameter of about 14 percent.

Perigee is set to occur at 6:22AM ET. But the Moon will be extra luminous tonight and Monday night for those in the US who don't want to get up that early.

This is the closest a full moon has to come to hitting perigee on the nose since January 26th, 1948, and the closest it will come for another 18 years, until November 25th, 2034.

What makes the November 14th moon so special is that it turns full at 1:52pm UTC (143:52am ET), two and a half hours after hitting perigee at 11:23 UTC (7:52am ET).

"They're the forgotten faces," said Tammy Gold, a family therapist and author of "Secrets of the Nanny Whisperer: A Practical Guide for Finding and Achieving the Gold Standard of Care for Your Child" (Perigee, 2015).

The natural satellite doesn't move around Earth in a perfect circle, which means that occasionally the moon will hit full phase when it is at its closest point (perigee) or farthest point (apogee) from the planet.

This was partly due to the rapidly dropping pressure of the storm, which made it intensify rapidly, and the fact that there had been a "supermoon," or a moon at perigee, or its closest point to Earth.

Either one of the new books should be a cause for celebration; both entering the world in such a short time frame has something of the power of an astronomical coincidence — like a lunar eclipse with the moon at perigee.

Each time the moon orbits the Earth, every 29.5 days, it will reach a close point to the Earth (perigee), and a far point (apogee), and occasionally, the close point will be close to the date of the full moon or new moon, a supermoon.

Not only is pre-dawn the closest to the full moon perigee us East Coasters are going to get, but—added bonus—as the moon sets, it can appear unnaturally large, owing to the fact that your brain starts measuring it against other objects on the horizon.

"Now, we tried sometimes not to sit next to Buzz at a party because he was working 24 hours, around the clock, with 'now, if you get an ellipse and its epicenter is incongruent with the other, and then of course this comes through and the perigee is down there,' " Collins said.

" (To ensure the cubesat avoids the most crowded areas of Earth's orbit.) "The perigee (closest point in orbit to earth) will be raised from ~185km to ~2100km and the apogee (farthest point in orbit to earth) will be reduced by ~200km for two reasons; to stay in a stable orbit that will not decay, and to abide by the 25-year NASA orbital debris rule where a spacecraft must not be in Low Earth Orbit, LEO (up to 2000 km) or Geosynchronous Orbit, GEO (35,786 km) for more than 25 years.

Occurring 3.6 days after perigee (Perigee on June 5, 1918), the moon's apparent diameter was larger.

Occurring only 4.4 days after perigee (Perigee on February 6, 2017), the moon's apparent diameter was larger.

Subsequent perigee-up operation moved its orbit to apogee 32110 km, perigee 460 km of 565 minutes period.

The term perigee-syzygy or perigee full/new moon is preferred in the scientific community. Perigee is the point at which the Moon is closest in its orbit to the Earth, and syzygy is when the Earth, the Moon and the Sun are aligned, which happens at every full or new moon. Astrophysicist Fred Espenak uses Nolle's definition but preferring the label of full Moon at perigee on full moons occurring "within 90% of its closest approach to Earth in a given orbit" over Nolle's calculations based on the closest of all orbits during the solar year. Wood used the definition of a full or new moon occurring within 24 hours of perigee and also used the label perigee-syzygy.

In the 1990s, Stiles edited a series of anthologies of primary sources on American history. These included The Citizen's Handbook (New York: Berkley Publishing Group, 1994); In Their Own Words: Civil War Commanders (New York: Perigee Books, 1995), In Their Own Words: Warriors and Pioneers (New York: Perigee Books, 1996), In Their Own Words: Robber Barons and Radicals (New York: Perigee Books, 1997), In Their Own Words: The Colonizers (New York: Perigee Books, 1998), and In Their Own Words: Founding Fathers (New York: Perigee Books, 1999), later republished as The American Revolution. Stiles also wrote for periodicals, authoring pieces for Smithsonian, Denver Post, and the Los Angeles Times.

An argument of perigee of 270° places apogee at the northernmost point of the orbit. An argument of perigee of 90° would likewise serve the high southern latitudes. An argument of perigee of 0° or 180° would cause the satellite to dwell over the equator, but there would be little point to this as this could be better done with a conventional geostationary orbit.

The path of totality crossed central Africa, southern India, and into China at sunset. The southern part of Mount Kilimanjaro, the highest mountain in Africa, also lies in the path of totality. Occurring only about 24 hours before perigee (Perigee on February 17, 1980), the Moon's apparent diameter was larger. This was a Supermoon Total Solar Eclipse because the Moon was just a day before perigee.

Most launch vehicles place geostationary satellites directly into a geostationary transfer orbit (GTO), an elliptical orbit with an apogee at GEO height and a low perigee. On-board satellite propulsion is then used to raise the perigee, circularise and reach GEO.

Mitz, Rick. The Great TV Sitcom Book. New York: Perigee Books, 1988. page 292Moritz, Charles.

As of it was located in an orbit with a perigee of , an apogee of , inclined at degrees to the equator. It has an orbital period of minutes, with right ascension of the ascending node of degrees and an argument of perigee of degrees.

Occurring only 3.2 days after perigee (Perigee on Friday, August 18, 2017), the moon's apparent diameter was larger during the total solar eclipse on Monday, August 21, 2017. There was another solar eclipse in 2017, a large annular solar eclipse (99.223%) on February 26.

The perigean tides are the spring tides that occur soon after the Moon passes its perigee.

The ground track of a Molniya orbit If the argument of perigee is zero, meaning that perigee and apogee lie in the equatorial plane, then the ground track of the satellite will appear the same above and below the equator (i.e., it will exhibit 180° rotational symmetry about the orbital nodes.) If the argument of perigee is non-zero, however, the satellite will behave differently in the northern and southern hemispheres. The Molniya orbit, with an argument of perigee near −90°, is an example of such a case. In a Molniya orbit, apogee occurs at a high latitude (63°), and the orbit is highly eccentric (e = 0.72).

Medved, Harry and Medved, Michael. The Golden Turkey Awards. Perigee Books, G.P. Putnam's Sons. New York. 1980. .

Occurring only 3.1 days after perigee (Perigee on June 27, 1954), the Moon's apparent diameter was larger. Totality lasted 2 minutes and 34.93 seconds, but at sunrise 1 minute and 8.6 seconds and at sunset 1 minute and 5.3 seconds. The moon's apparent diameter was larger, 1930.2 arc-seconds.

SBS F6 Prime brochure, Hughes Space and Communications Group 856268/6-85/10M The perigee motor provided energy (velocity) to the satellite to raise the apogee of the satellite's orbit; it is named for the location in the orbit at which it is used. The perigee motor was jettisoned after it was used. The liquid fuel apogee engines of the Intelsat VI satellites were then used to boost the perigee of the satellite and provide orbit circularization through apogee burns.

The operator attempted to perform an emergency move of the spacecraft to a graveyard orbit, but evidently, only the apogee engine burn was successful while the perigee burn failed. It is suggested that the spacecraft may have run out of power during the perigee attempt, or that it may have exhausted its fuel supply. , VeneSat-1 was in an elliptical orbit of approximately , which placed its perigee approximately above the normal geosynchronous orbit. It had also drifted west by 30°.

Therefore, the Moon takes a little longer to return to perigee than to return to the same star.

The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books; , pg. 170.

Totality was visible in Indonesia, Papua New Guinea and southern Pacific Ocean. West of the International Date Line the eclipse took place on November 23, including all land in the path of totality. Occurring only 2.1 days after perigee (Perigee on November 20, 1984), the Moon's apparent diameter was fairly larger.

AEHF-2 used a chemical engine to raise perigee to 10,150 miles and proceeded to geosynchronous orbit using electric propulsion.

The Falcon 9 upper stage used to launch AsiaSat 8 is derelict in a decaying elliptical low- Earth orbit that, , had an initial perigee of and an initial apogee of . One month on, the orbit had decayed to an altitude of at its closest approach to Earth, and by November had decayed to a perigee.

Figure 1: The Molniya orbit. Usually the period from perigee +2 hours to perigee +10 hours is used to transmit to the northern hemisphere. SDS constellation, which uses satellites in a mixture of geostationary and Molniya orbits. The constellation of Molniya-orbiting satellites uses three satellites on different orbital planes, with apogees comparable to those of the geostationary satellites.

To maximise the dwell time the eccentricity, the differences in altitudes of the apogee and perigee, had to be large. However, the perigee needed to be far enough above the atmosphere to avoid drag, and the orbital period needed to be approximately half a sidereal day. These two factors constrained the eccentricity to become approximately 0.737.

Occurring only 4.7 days before perigee (Perigee on March 3, 2017), the Moon's apparent diameter was larger. The moon's apparent diameter was just over 0.7% smaller than the Sun's. February 26 is the 57th day of the year in Gregorian Calendar. It was visible across southern South America in the morning and ended in south-western Africa at sunset.

This film was re-released in 1950.Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books.

Perigee Books. . P. 1250. for best actress in a comedy series. After Father Knows Best, Wyatt guest-starred in several other series.

TecSAR was placed into a Low Earth orbit with an apogee of , a perigee of , and an equatorial inclination of 41 degrees.

ESSA-2 had an inclination of 101.3°, and an orbited the earth once every 113 minutes. Its perigee was and its apogee was .

The satellite orbited the Earth once every 1 hour and 38 minutes, at an inclination of 98.6°. Its perigee was and apogee was .

On 26 May 1999, it had a perigee of , an apogee of , an inclination of 99.0°, and an orbital period of 99.0 minutes.

The team went without an agent for two years.Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books.

A total solar eclipse occurred on May 29, 1919. With the duration of totality at maximum eclipse of 6 minutes 50.75 seconds, it was the longest solar eclipse since May 27, 1416. A longer total solar eclipse would later occur on June 8, 1937. Occurring only 0.8 days after perigee (Perigee on May 28, 1919), the Moon's apparent diameter was larger.

The path of annularity crossed Chile, Argentina, South Africa, southern Basutoland (today's Lesotho) and Malagasy Republic (today's Madagascar). Occurring 3.7 days before perigee (Perigee on January 29, 1963), the Moon's apparent diamater was larger. The moon was 374,860 km (232,927 mi) from the Earth. The moon's apparent diameter was 4.8 arcseconds larger than the July 20, 1963 total solar eclipse.

Three of the shuttle astronauts successfully captured the satellite by hand on May 14, 1992, after several failed attempts using a capture bar. After being secured in the shuttle cargo bay, a new perigee kick motor was installed. Intelsat 603 was released from the shuttle and the perigee kick motor was successfully ignited and 603 was placed into the proper geostationary orbit.

Occurring only 48 hours before perigee (Perigee on June 13, 1983), the Moon's apparent diameter was larger. The path of totality went through Christmas Islands, Indonesia, Papua New Guinea, and terminated in Vanuatu. Maximum eclipse occurred off the Indonesian island of Madura. Major Indonesian cities witnessed totality, including Yogyakarta, Semarang, Surabaya, and Makassar, in addition to Port Moresby in Papua New Guinea.

The launch placed both satellites into geosynchronous transfer orbits with perigee altitudes of about and apogee altitudes of approximately at inclinations of about 3°.

A total solar eclipse will occur at the Moon's descending node of the orbit on August 12, 2026, 2 days past perigee (Perigee on Monday, August 10, 2026), in North America and Europe. The total eclipse will pass over the Arctic, Greenland, Iceland, Atlantic Ocean and northern Spain. The points of greatest duration and greatest eclipse will be just 45 km off the western coast of Iceland by 65°10.3' N and 25°12.3' W, where the totality will last 2m 18.21s. It will be the first total eclipse visible in Iceland since June 30, 1954, also Solar Saros series 126 (descending node), and the only one to occur in the 21st century as the next one will be in 2196. Occurring only 2.3 days after perigee (Perigee on August 10, 2026), the Moon's apparent diameter will be larger.

Born in Chicago, Illinois,Katz, Ephraim (1979). The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books. . P. 973.

Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books. The film was budgeted at $652,933 but came $41,900 under.

It is currently in a geostationary orbit, with an apogee of , a perigee of , zero degrees of inclination, and an orbital period of 24 hours.

On October 20 it performed the second orbital maneuver increasing its perigee to while reducing the inclination to 1.52°. On October 22 the third maneuver increased the perigee to and reduced the inclination to less than 1°. On October 24 and 25 it performed the fourth and fifth maneuvers finally reaching the geostationary orbit. On October 27 the LAE was disabled to prevent inadvertent ignitions.

Annularity was visible in Mexico, the United States, Azores Islands, Morocco and Algeria. It was the first annular solar eclipse visible in the US in 33 years. The moon's apparent diameter was near the average diameter because occurs 6.7 days after apogee (Apogee on May 24, 1984 at 01:00 UTC) and 7.8 days before perigee (Perigee on June 7, 1984 at 11:15 UTC).

A juxtaposition of the apparent diameters of an average full moon on December 20, 2010 (left), and of the supermoon of March 19, 2011 (right) as viewed from Earth. A supermoon is a full moon or a new moon that nearly coincides with perigee—the closest that the Moon comes to the Earth in its elliptic orbit—resulting in a slightly larger-than-usual apparent size of the lunar disk as viewed from Earth. The technical name is a perigee syzygy (of the Earth–Moon–Sun system) or a full (or new) Moon around perigee. The term supermoon is astrological in origin and has no precise astronomical definition.

It was decided to launch Superbird-6 into a 2,895 minutes period supersynchronous orbit with an apogee of 120,679 km, a perigee of 1,138 km and a 25.5° inclination. This extreme perigee and a six-maneuvers circularization program would reduce the propellant expenditure to its final position in geosynchronous orbit. It was launched on April 16, 2004 by an Atlas IIAS that injected in the supersynchronous orbit specified by the satellite manufacturer, at which point it was named Superbird-A2. But the orbit analysis had failed to take into consideration the influence of the Moon at such high apogees and the perigee started to drop dangerously fast.

Principal photography took place between August 1 and August 28, 1952.Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books.

Two weeks after the settlement, they re-signed with Universal through 1955.Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books.

Mary Elizabeth Hughes (November 13, 1919 Katz, Ephraim (1979). The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books. . P. 586.

As of February 3, 2014 it remains in orbit, with a perigee of , an apogee of , inclination of 18.63 degrees and an orbital period of 28.25 hours.

The Moon's orbit approximates an ellipse rather than a circle. The orientation and the shape of this orbit is not fixed. In particular, the positions of the extreme points, the point of closest approach (perigee) and the point of farthest excursion (apogee), make a full circle in about nine years. It takes the Moon longer to return to the same position, perigee or apogee, because it moved ahead during one revolution.

Intelsat 603 was launched by a Commercial Titan III on 14 March 1990. The separation of the upper (second) stage from the satellite failed. This left the satellite and the upper stage attached to each other, and Intelsat was unable to fire the perigee motor to boost the satellite to its higher orbit. Intelsat flight controllers jettisoned the perigee motor which detached the satellite from the Titan upper stage.

Occurring only 18 hours and 35 minutes after perigee (Perigee on February 25, 1979 at 22:19 UTC), the Moon's apparent diameter was larger. The central shadow of the moon passed through the American states of Washington, Oregon, Idaho, Montana (where totality covered almost the entire state), and North Dakota, the Canadian provinces Saskatchewan, Manitoba, Ontario, and Quebec, the Northwest Territories of Canada (the portion that is now Nunavut), and Greenland.

Wong's second book entitled The Real Cost of Living: Making the Best Decisions for You, Your Life and Your Money was released by Perigee/Penguin in December 2010.

Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books. The camera crew can be heard laughing in the background during the routine.

The IBEX satellite, initially launched into a highly-elliptical transfer orbit with a low perigee, used a solid fuel rocket motor as its final boost stage at apogee, in order to raise its perigee greatly and to achieve its desired high-altitude elliptical orbit. IBEX is in a highly-eccentric elliptical terrestrial orbit, which ranges from a perigee of about to an apogee of about . Its original orbit was about —that is, about 80% of the distance to the Moon—which has changed primarily due to an intentional adjustment to prolong the spacecraft's useful life (see Orbit adjusted below). This very high orbit allows the IBEX satellite to move out of the Earth's magnetosphere when making scientific observations.

They were both suspended for a week, and filming began only two days behind schedule.Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books.

Every 13.7 days at its perigee of , TESS will downlink to Earth over a period of approximately 3 hours the data it has collected during the just finished orbit.

In these expressions, the symbols l, l', F and D refer to an alternative set of fundamental angular arguments (usually preferred for use in modern lunar theory), in which:- :l is the mean anomaly of the Moon (distance from its perigee). :l' is the mean anomaly of the Sun (distance from its perigee). :F is the Moon's mean argument of latitude (distance from its node). :D is the Moon's mean elongation (distance from the sun).

The continental path of totality fell entirely within the Soviet Union, belonging to Georgia, Kazakhstan and Russia today. The southern part of Mount Elbrus, the highest mountain in Europe, also lies in the path of totality. Occurring only 3.8 days after perigee (Perigee on July 27, 1981), the Moon's apparent diameter was larger. With a path width of 107.8 km (66.984 mi, or 353,674.541 feet), this total solar eclipse had an average path.

A total lunar eclipse took place on October 8, 2014. It is the second of two total lunar eclipses in 2014, and the second in a tetrad (four total lunar eclipses in series). Other eclipses in the tetrad are those of April 15, 2014, April 4, 2015, and September 28, 2015. Occurring only 2.1 days after perigee (Perigee on October 6, 2014), the Moon's apparent diameter was larger, 1960.6 arcseconds (32 arcminutes, 40.6 arcseconds).

The launch successfully placed EchoStar XV into a geosynchronous transfer orbit. Following separation from the rocket, it manoeuvred into a geostationary orbit with a perigee of and an apogee of .

Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books. There is a joke used in the film that is often attributed to Benjamin Franklin.

As of it was in an orbit with a perigee of , an apogee of and a 98.2° inclination. The mission is expected to cost , including design, development, launch and operations.

The Movie Guide, Perigee Books, 1992. Both films were completed in a total of six weeks of continuous shooting (three weeks per film).Peary, Danny. Cult Movies, Delta Books, 1981.

Abbott and Costello Meet Captain Kidd was filmed from February 27 through March 25, 1952.Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books.

Perigee Books. , p. 591. Her father, George R. Hussey, died of the Spanish flu in 1918 when she was seven years old. Ten years later, her mother, Julia Corbett Hussey,U.

The film premiered in Costello's hometown of Paterson, New Jersey at a benefit for St. Anthony's Church.Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books.

The total mass placed in orbit was 33,895 pounds (15,375 kg). The perigee was 307.8 miles (495 km), the apogee was 461.9 miles (743 km), and the orbital inclination was 31.76°.

UARS was decommissioned on 14 December 2005. The final perigee lowering burns lowered the orbit to 518 km x 381 km. They were followed by the passivation of the satellite's systems.

It ended up in a low Earth orbit with a perigee of , an apogee of , and 28.3 degrees of inclination. It had an orbital period of 96.4 minutes. Due to the low perigee of its orbit, Transit 3B decayed quickly, and reentered the atmosphere on 30 March 1961, less than 37 days after launch. Despite being in the wrong orbit and operating for less time than had been planned, some useful data was returned from the mission.

It ended up in a low Earth orbit with a perigee of , an apogee of , and 28.3 degrees of inclination. It had an orbital period of 96.4 minutes. Due to the low perigee of its orbit, LOFTI-1 decayed quickly, and reentered the atmosphere on 30 March 1961, less than 37 days after launch. Despite being in the wrong orbit and operating for less time than had been planned, some useful data was returned from the mission.

When launched by the U.S. Space Shuttle a solid propellant perigee stage (motor and carrier) would be attached to the bottom of the spacecraft. This carrier was used to mount the satellite into a cradle in the Space Shuttle cargo bay. The satellite was ejected from the space shuttle "Frisbee-style" which imparted a stabilizing spin to the satellite. The satellite was allowed to drift a safe distance from the space shuttle before the perigee motor was fired.

The Time of Their Lives was filmed at Universal Studios from March 6 through May 15, 1946.Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books.

Kosmos 133 was operated in a low Earth orbit, on 28 November 1966, it had a perigee of , an apogee of , an inclination of 51.9°, and an orbital period of 88.4 minutes.

John Hudson on TV's The Millionaire (1955) Nancy Gates (February 1, 1926Katz, Ephraim (1979). The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books. .P. 471.

Secondly, the occurrence of the September 28 lunar perigee-the point in the moon's monthly orbit when it is closest to the earth-meant that the spring tides were higher than normal.

The exact height of a satellite in a Tundra orbit varies between missions, but a typical orbit will have a perigee of approximately and an apogee of , for a semi-major axis of .

Abbott and Costello in Hollywood. New York: Perigee Books. In 1948, Abbott and Costello fired their agent, Eddie Sherman. Just before the filming of this picture, they reconciled with Sherman and rehired him.

Comin' Round the Mountain was filmed from January 15 through February 12, 1951 and shot almost entirely in sequence.Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books.

The exact height of a satellite in a Molniya orbit varies between missions, but a typical orbit will have a perigee of approximately and an apogee of , for a semi-major axis of .

Perigee Books, 1980. Colorful, theatrical Yippie actions were tailored to attract media coverage and also to provide a stage where people could express the "repressed" Yippie inside them.Jerry Rubin, Do It!, page 86.

Apsidal precession occurs when the direction of the major axis of the Moon's elliptic orbit rotates once every 8.85 years. The second kind of precession of the Moon's orbit is that of the major axis of the Moon's elliptic orbit (the line of the apsides from perigee to apogee), which precesses eastward by 360° in approximately 8.85 years. This is the reason that an anomalistic month (the period the Moon moves from the perigee to the apogee and to the perigee again) is longer than the sidereal month (the period the Moon takes to complete one orbit with respect to the fixed stars). This apsidal precession completes one rotation in the same time as the number of sidereal months exceeds the number of anomalistic months by exactly one, after about 3,233 days (8.85 years).

Kosmos 690 was launched on 22 October 1974 from Plesetsk Cosmodrome with a Soyuz-U rocket. It was placed in low earth orbit, with apogee of , perigee of and orbital inclination of 62.8 degrees.

The mission was planned to last 42 minutes and 17 seconds, placing the both satellites into geostationary transfer orbits with a perigee altitude of about and apogee of and an inclination of about 6 degrees.

"Abbott and Costello in Hollywood." Perigee, 1991. Conrad once revealed that CBS intended to do yearly TV revivals of The Wild Wild West."Robert Conrad Digs Macho Man Roles," The Hartford Courant, March 25, 1979.

Intelsat II F-1 remains in orbit. As of 1 February 2014 it was in an orbit with a perigee of , an apogee of , inclination of 16.97 degrees and an orbital period of 11.97 hours.

The eccentricity of the orbit is based on the differences in altitudes of its apogee and perigee. To maximise the amount of time that the satellite spends over the apogee, the eccentricity should be set as high as possible. However, the perigee needs to be high enough to keep the satellite substantially above the atmosphere to minimize drag (~600km), and the orbital period needs to be kept to approximately half a sidereal day (as above). These two factors constrain the eccentricity, which becomes approximately 0.737.

One month on, the orbit had decayed to an altitude of at its closest approach to Earth, and by November had decayed to a perigee. The derelict second stage reentered the atmosphere on 28 December 2014.

The mission was planned to last 33 minutes and 56 seconds, placing both satellites into a geostationary transfer orbit, with an apogee of about and a perigee of about , at an inclination of about 3 degrees.

It was operated in an orbit with a perigee of , an apogee of , an inclination of 49.0°, and an orbital period of 108.3 minutes. On 2 April 1967, it decayed from orbit and reentered the atmosphere.

It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.4°, and an orbital period of 108.6 minutes. On 8 March 1968, it decayed from orbit and reentered the atmosphere.

It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.5°, and an orbital period of 99.8 minutes. On 30 November 1966, it decayed from orbit and reentered the atmosphere.

It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.4°, and an orbital period of 100.3 minutes. On 6 July 1967, it decayed from orbit and reentered the atmosphere.

It was operated in an orbit with a perigee of , an apogee of , 48.4 degrees of inclination, and an orbital period of 99 minutes. On 5 May 1969, it decayed from orbit and reentered the atmosphere.

Gardiner was born in Wimbledon, England, and he was a graduate of the Royal Academy of Dramatic Art.Katz, Ephraim (1979). The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books. .

It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.5°, and an orbital period of 91.5 minutes. On 30 January 1968, it decayed from orbit and reentered the atmosphere.

It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.4°, and an orbital period of 91.5 minutes. On 24 March 1968, it decayed from orbit and reentered the atmosphere.

It was operated in an orbit with a perigee of , an apogee of , an 48.4° of inclination, and an orbital period of 91.7 minutes. On 3 January 1966, it decayed from orbit and reentered the atmosphere.

It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.4°, and an orbital period of 91.7 minutes. On 18 January 1966, it decayed from orbit and reentered the atmosphere.

The mission was planned to last 35 minutes and 7 seconds, placing both satellites into a super-synchronous transfer orbit, with an apogee of about and a perigee of about , at an inclination of about 3 degrees.

Variety, too, very much liked Beery in the film, noting that he delivered a "studied, adult" performance.O'Neil, Thomas. Movie Awards: The Ultimate, Unofficial Guide to the Oscars, Golden Globes, Critics, Guild & Indie Honors. New York: Perigee, 2003.

The argument of perigee is set at 270°, causing the satellite to experience apogee at the most northerly point of its orbit. For any future applications over the southern hemisphere, it would instead be set at 90°.

Studies found that this could be achieved using a large elliptical orbit, with an apogee over Russian territory. The satellite's name, "quick as lightning", is in reference to the speed with which is passes through the perigee.

Dana was born in New York City and graduated from Barnard College and the Royal Academy of Dramatic Art.Katz, Ephraim (1979). The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books. .

It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.4°, and an orbital period of 93.1 minutes. It decayed from its orbit and reentered the atmosphere on 11 October 1967.

Its perigee to Earth is 829 kilometers. Its apogee is 845 kilometers away from Earth. Its inclination is 98.70 degrees. It was managed by the U.S. National Oceanic and Atmospheric Administration (NOAA); designed and launched by NASA.

In 1943, Corday announced her engagement to Navy Ensign Marshall Buell. She married producer Harold Nebenzal Katz, Ephraim (1979). The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books. . P.273.

Nozomi was launched on July 3, 1998. After launch on the third M-V launch vehicle, Nozomi was put into an elliptical geocentric parking orbit with a perigee of 340 km and an apogee of 400,000 km.

The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books. . P. 81. During the transition from silent films to sound, an employee at MGM hired Barnett to prank Louis B. Mayer.

This allows a fixed nozzle, which saves cost and weight versus a hot joint. A single-impulse launch results in an elliptical orbit, with a high apogee and low perigee. The use of three stages, plus the coast period between second- and third-stage firings, help to circularize the orbit, ensuring the perigee clears the Earth's atmosphere. If the Pegasus launch had begun at low altitude, the coast period or thrust profile of the stages would have to be modified to prevent skimming of the atmosphere after one pass.

Totality was visible from Hokkaido in Japan and Kuril Islands in Soviet Union (now belonging to Russia) on July 21, and Alaska, and Maine in the United States and also Canada on July 20. Astronomer Charles H. Smiley observed the eclipse from a U.S. Air Force F-104D Starfighter supersonic aircraft that was "racing the moon's shadow" at extending the duration of totality to 4 minutes 3 seconds. The moon was 375,819 km (233,523 mi) from the Earth. Occurring about 4.1 days after perigee (Perigee on July 16, 1963), the Moon’s apparent diameter was larger.

This annular solar eclipse was large because the Moon covered 99.4% of the Sun, with a path width of only 25 km (15.534 mi, or 82,080.997 feet). It was visible in Australia, crossing over Tasmania and southern Stewart Island of New Zealand near sunrise on February 5th (Thursday), and ended at sunset over western South America on February 4th (Wednesday). Occurring only 4 days before perigee (Perigee on February 8, 1981), the moon's apparent diameter was larger. The moon's apparent diameter was 7 arcseconds smaller than the July 31, 1981 total solar eclipse.

A total solar eclipse occurred at the ascending node of the Moon's orbit on July 2, 2019, with an eclipse magnitude of 1.0459. Totality was visible from the southern Pacific Ocean east of New Zealand to the Coquimbo Region in Chile and Central Argentina at sunset, with the maximum of 4 minutes 32 seconds visible from the Pacific Ocean. The Moon was only 2.4 days before perigee (Perigee on July 5, 2019), making it fairly large. Another solar eclipse occurred one lunar year after this eclipse, on June 21, 2020.

The Molniya orbit was discovered by Soviet scientists in the 1960s as a high-latitude communications alternative to geostationary orbits, which require large launch energies to achieve a high perigee and to change inclination to orbit over the equator (especially when launched from Russian latitudes). As a result, OKB-1 sought a less energy- demanding orbit. Studies found that this could be achieved using a highly elliptical orbit with an apogee over Russian territory. The orbit's name refers to the "lightning" speed with which the satellite passes through the perigee.

GTO is a highly elliptical Earth orbit with an apogee of , or above sea level, which corresponds to the geostationary altitude. The period of a standard geosynchronous transfer orbit is about 10.5 hours. The argument of perigee is such that apogee occurs on or near the equator. Perigee can be anywhere above the atmosphere, but is usually restricted to a few hundred kilometers above the Earth's surface to reduce launcher delta-V (\Delta V) requirements and to limit the orbital lifetime of the spent booster so as to curtail space junk.

Most launch vehicles place geosynchronous satellites directly into a geosynchronous transfer orbit (GTO), an elliptical orbit with an apogee at GSO height and a low perigee. On-board satellite propulsion is then used to raise the perigee, circularise and reach GSO. Once in a viable geostationary orbit, spacecraft can change their longitudinal position by adjusting their semi-major axis such that the new period is shorter or longer than a sidereal day, in order to effect an apparent "drift" Eastward or Westward, respectively. Once at the desired longitude, the spacecraft's period is restored to geosynchronous.

Unfortunately, without the fourth stage burn, the spacecraft lowered its perigee back into the Earth's atmosphere causing reentry. The fourth stage re-entered on a later orbit. There is disagreement between American and Russian sources on the timeline.

After completion of this film, Abbott and Costello began a tour of the United States to help promote the selling of U.S. War Bonds.Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books.

Brown, 1919. It arises from an approximately six-monthly periodic variation of the eccentricity of the Moon's orbit and a libration of similar period in the position of the Moon's perigee, caused by the action of the Sun.

It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.5°, and an orbital period of 93.5 minutes. It decayed from its orbit and reentered in the atmosphere on 12 April 1967.

The spacecraft was placed in a standby status November 25, 1969, and all support was terminated November 1, 1971. By April 1970 the spacecraft perigee had increased to 46,000 km and the inclination had increased to 58.8 deg.

In 1952, an unused treatment they wrote for a service comedy at Paramount around 1943 was later adapted as Jumping Jacks for another comic duo, Martin and Lewis.Furmanek, Bob, and Ron Palumbo. "Abbott and Costello in Hollywood." Perigee, 1991.

Nimbus 5 was launched on December 11, 1972, by a Delta rocket from Vandenberg Air Force Base, California, USA. The satellite orbited the Earth once every 107 minutes, at an inclination of 99°. Its perigee was and apogee was .

Bey was an acting student at Ben Bard's School of Dramatic Art and was active in the Pasadena Playhouse.Katz, Ephraim (1979). The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books. . P.118.

It will operate in a Molniya orbit with a perigee of , an apogee of , and 65° inclination. Based on radio observations, Meridian-2 is known to downlink in the 278 MHz, 992 MHz-1002 MHz and 3.6 GHz bands.

It was operated in an orbit with a perigee of , an apogee of , 48.4 degrees of inclination, and an orbital period of 108.2 minutes. It remained in orbit until it decayed and reentered the atmosphere on 9 May 1974.

Intelsat III F-2 remains in orbit as a derelict satellite. As of February 7, 2014 it was in an orbit with a perigee of , an apogee of , inclination of 13.73 degrees and an orbital period of 26.60 hours.

Data were read with alternate 70 ms and 30 ms integrations for 5 intervals every 320 ms. TD-1A was put in a nearly circular polar sun-synchronous orbit, with apogee 545 km, perigee 533 km, and inclination 97.6°.

The radius of geostationary orbit, is within 0.02% of the variation of the distance of the moon in a month (the difference between its apogee and perigee), , and 5% error of the length of the equator, . Similarly, Earth's escape velocity is .

Nimbus 6 was launched on June 12, 1975, by a Delta rocket from Vandenberg Air Force Base, California, United States. The satellite orbited the Earth once every 107 minutes, at an inclination of 100°. Its perigee was and apogee was .

It was operated in an orbit with a perigee of , an apogee of , 48.4° of inclination, and an orbital period of 104.7 minutes. It completed operations on 28 February 1969, before decaying from orbit and reentering the atmosphere on 2 March.

ASTRO-G (also known as VSOP-2, and very rarely called VSOP-B) was a planned radio telescope satellite by JAXA. It was expected to be launched into elliptic orbit around Earth (apogee height 25,000 km, perigee height 1,000 km).

Pryor's debut on stage came in stock theater when he was 18, after which he worked with several repertory theatre companies.Katz, Ephraim (1979). The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books. . P. 936.

Ariel 4 was placed into a low Earth orbit, with a perigee of , an apogee of , 82.9 degrees of inclination and an orbital period of 95.3 minutes as of 10 January 1972. It decayed from orbit on 12 December 1978.

Calhern died at age 61 of a sudden heart attack in Nara, Japan, while there to film The Teahouse of the August Moon.Katz, Ephraim (1979). The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books. .

Science fiction author Robert A. Heinlein wrote a film treatment in 1950 called Abbott and Costello Move to the Moon that may have inspired the film's screenplay.Furmanek, Bob and Ron Palumbo (1991). Abbott and Costello in Hollywood. New York: Perigee Books.

A total solar eclipse occurred on July 10, 1972. A solar eclipse occurs when the Moon passes between Earth and the Sun, thereby totally or partly obscuring the image of the Sun for a viewer on Earth. A total solar eclipse occurs when the Moon's apparent diameter is larger than the Sun's, blocking all direct sunlight, turning day into darkness. Totality occurs in a narrow path across Earth's surface, with the partial solar eclipse visible over a surrounding region thousands of kilometres wide. Occurring only 2.9 days after perigee (Perigee on July 7, 1972), the Moon’s diameter was a relatively large.

Elektron 3 and 4 were launched on July 11, 1964 at 21:51:02 UTC from Launch Complex 1 at Baikonur Space Center, again on a single Vostok 8K72K, with identical missions and similar orbits to that of Elektron 1 and 2. Elektron 3's orbit had a perigee of , an apogee of , an orbital inclination of 61°, and a period of 168 minutes; Elektron 4's orbit had a perigee of , an apogee of , an orbital inclination of 61°, and a period of 1,314 minutes. Elektron 3 returned usable data as late as October 1964; Elektron 4 as late as November 1964.

A penumbral lunar eclipse took place on January 20, 1981. In a rare total penumbral eclipse, the entire Moon was partially shaded by the Earth (though none of it was in complete shadow), and the shading across the Moon should have been quite visible at maximum eclipse. The penumbral phase lasted for 4 hours and 24 minutes in all, though for most of it, the eclipse was extremely difficult or impossible to see. The moon's apparent diameter was larger because the eclipse occurred 5.2 days after perigee (Perigee on approximately 1981 Jan 15 at 03:01:56.7 UTC).

It is 27.32158 days, very slightly shorter than the sidereal month (27.32166) days, because of precession of the equinoxes. # An anomalistic month is the average time the Moon takes to go from perigee to perigee—the point in the Moon's orbit when it is closest to Earth. An anomalistic month is about 27.55455 days on average. # The draconic month, draconitic month, or nodal month is the period in which the Moon returns to the same node of its orbit; the nodes are the two points where the Moon's orbit crosses the plane of the Earth's orbit.

The orbit of the Moon is a nearly circular ellipse about the Earth (the semimajor and semiminor axes are 384,400 km and 383,800 km, respectively: a difference of only 0.16%). The equation of the ellipse yields an eccentricity of 0.0549 and perigee and apogee distances of 362,600 km and 405,400 km respectively (a difference of 12%). Since nearer objects appear larger, the Moon's apparent size changes as it moves toward and away from an observer on Earth. An event referred to as a 'supermoon' occurs when the full Moon is at its closest to Earth (perigee).

A total lunar eclipse occurred on the evening of Wednesday, February 20, and morning of Thursday, February 21, 2008. It was visible in the eastern evening sky on February 20 for all of North and South America, and on February 21 in the predawn western sky from most of Africa and Europe. Greatest Eclipse occurring on Thursday, February 21, 2008 at 03:26:03 UTC, totality lasting 49 minutes and 45.6 seconds. Occurring 7.1 days after perigee (Perigee on February 14, 2008) and 6.9 days before apogee (Apogee on February 28, 2008), the Moon's apparent diameter was near the average diameter.

The gravitational force is greatest when the Moon is at perigee — closest to Earth — and least when it is at apogee — farthest from Earth — about two weeks after perigee. The Moon has a larger effect on the tides than the Sun, but the Sun's position also has an influence on the tides. Earth moves around the Sun in an elliptic orbit that takes a little over 365 days to complete. Its gravitational force is greatest when the Earth is at perihelion — closest to the Sun in early January — and least when the Earth is at aphelion — farthest from the Sun in early July.

Low tide at Bangchuidao scenic area, Dalian, Liaoning Province, China Ocean Beach in San Francisco, California, U.S. Bar Harbor, Maine, U.S. (2014) The changing distance separating the Moon and Earth also affects tide heights. When the Moon is closest, at perigee, the range increases, and when it is at apogee, the range shrinks. Every lunations (the full cycles from full moon to new to full), perigee coincides with either a new or full moon causing perigean spring tides with the largest tidal range. Even at its most powerful this force is still weak, causing tidal differences of inches at most.

Totality was visible in Peru, northern Chile, Bolivia, northern Argentina, Paraguay including the northeastern part of its capital Asunción, Brazil and Gough Island of British overseas territory of Saint Helena, Ascension and Tristan da Cunha. The Iguazu Falls, one of the largest waterfalls systems in the world, also lies in the path of totality. Totality lasted about 4.4 minutes, so it was a relatively long total solar eclipse. Occurring only 10 hours and 2 minutes before perigee (Perigee on November 3, 1994 at 23:41 UTC, while greatest eclipse at 13:39 UTC), the moon's apparent diameter was too larger.

Aerocapture has not yet been tried on a planetary mission, but the re-entry skip by Zond 6 and Zond 7 upon lunar return were aerocapture maneuvers, since they turned a hyperbolic orbit into an elliptical orbit. On these missions, since there was no attempt to raise the perigee after the aerocapture, the resulting orbit still intersected the atmosphere, and re- entry occurred at the next perigee. Aerocapture was originally planned for the Mars Odyssey orbiter, but later changed to aerobraking for reasons of cost and commonality with other missions. Aerocapture has been proposed and analyzed for arrival at Saturn's moon Titan.

Between different full moons, the Moon's angular diameter can vary from 29.43 arcminutes at apogee to 33.5 arcminutes at perigee—an increase of around 14% in apparent diameter or 30% in apparent area. This is because of the eccentricity of the Moon's orbit.

The satellite was launched southeast over the Indian Ocean to avoid overflying neighboring countries and was placed into an orbit with an inclination of 55.5 degrees, with a perigee of 246 km, an apogee of 377 km, and a period of 90.76 minutes.

It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.8°, and an orbital period of 104.3 minutes. It completed operations on 12 May 1967, before decaying from orbit and reentering the atmosphere on 23 November 1967.

It was operated in an orbit with a perigee of , an apogee of , 48.4 degrees of inclination, and an orbital period of 94.6 minutes. It completed operations on 3 May 1969, before decaying from orbit and reentering the atmosphere on 18 July.

She is the author of a non-fiction book, The Extraordinary Catalog of Peculiar Inventions: The Curious World of the Demoulin Brothers and Their Fraternal Lodge Prank Machines from Human Centipedes and Revolving Goats to Electric Carpets and Smoking Camels (Perigee, 2011).

The spacecraft was first launched by Vega flight VV06 into an elliptical LEO parking orbit. From there it executed a short burn each time perigee was passed, slowly raising the apogee closer to the intended halo orbit around the Earth–Sun point.

Perigee Books. . P. 1215. with interests in music and won beauty contests at both schools. Weaver began her acting career as a stage actress in the early 1930s, and also worked as a model during that period, as well as a singer.

New York: Perigee Books. A nine-year-old Harry Shearer appears as a kid at the orphanage. Shortly after the film's release, Abbott and Costello appeared on The Colgate Comedy Hour and did a comedy sketch in which they attended the film's premiere.

Douglas was married five times – to Elizabeth Farnum, Susie Wells, and Gerri Higgins, and to actresses Virginia Field and Jan Sterling.Katz, Ephraim (1979). The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books. . pp. 355–356.

It was operated in an orbit with a perigee of , an apogee of , an inclination of 49.0°, and an orbital period of 95.5 minutes. It completed operations on 7 February 1968. On 7 July 1968, it decayed from orbit and reentered the atmosphere.

It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.9°, and an orbital period of 95.3 minutes. It completed operations on 26 February 1966. On 21 November 1966, it decayed from orbit and reentered the atmosphere.

It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.5°, and an orbital period of 91.1 minutes. It completed operations on 6 June 1968. On 30 June 1968, it decayed from orbit and reentered the atmosphere.

In Argentina, the best places to see the eclipse were located in the south of the Chubut Province, in the towns of Facundo, Sarmiento and Camarones. Lunar Perigee occurred at about 2017 Mar 03 at 07:41:24.5 UTC, 4.7 days later.

Solrad 10 was launched on 8 July 1971 from Wallops Flight Facility, Virginia, with a Scout rocket. When it was launched, it had an orbit with of apogee, of perigee, 51.1 degrees of orbital inclination and 1 hour and 35 minutes of orbital period.

New York: Perigee Books. It was during filming that Abbott and Costello had their hand and footprints enshrined at Grauman's Chinese Theater on the night of Dec. 8, 1941. Abbott and Costello also signed a new agreement regarding their partnership on January 9, 1942.

Kosmos 225 was operated in an orbit with a perigee of , an apogee of , an inclination of 48.4°, and an orbital period of 92.2 minutes. It completed operations on 29 June 1968, before decaying from orbit and reentering the atmosphere on 2 November 1968.

The adaptor connecting the Gemini spacecraft to OPS 0855 contained three additional spacecraft, two OV4-1 satellites, and OV1-6. These were released into low Earth orbit. OPS 0855 entered an orbit with an apogee of , a perigee of , and 32.82 degrees of inclination.

In August 1993 it was decommissioned and raised to a graveyard orbit slightly above geosynchronous altitude. As of 14 November 2013, it is in an orbit with a perigee of , an apogee of , inclination of 14.69 degrees and an orbital period of 23.93 hours.

The Encyclopedia of Film. New York: Perigee, 1991. Print. Margaret Markov, who plays Karen Brent, had appeared in The Hot Box (1972), which was also a Latin American prison film. All of these movie were shot in the Philippines in accordance with their low budgets.

The greatest eclipse occurred exactly at perigee. Totality started in Ethiopia, Italian Somaliland (today's Somalia), and passed British Maldives and Christmas Island in the Straits Settlements (now in Australia) in the Indian Ocean, and Australia. Two large scientific expeditions investigated Einstein's theory of relativity.

These findings have prompted the FAI to propose holding a joint conference with the International Astronautical Federation (IAF) in 2019 to "fully explore" the issue. Another definition proposed in international law discussions defines the lower boundary of space as the lowest perigee attainable by an orbiting space vehicle, but does not specify an altitude. This is the definition adopted by the U.S.military. Due to atmospheric drag, the lowest altitude at which an object in a circular orbit can complete at least one full revolution without propulsion is approximately , whereas an object can maintain an elliptical orbit with perigee as low as about without propulsion.

Arabian Peninsula (top left) and northeast Africa (bottom) as seen from the orbiting Gemini-11 spacecraft at an altitude of 340 nautical miles during its 27th revolution around Earth. (Taken with a modified 70 mm Hasselblad camera.) The direct-ascent rendezvous and docking with the Agena vehicle was achieved approximately 94 minutes after lift-off, depending on the on-board computer and radar equipment with only minimal assistance from ground support. Gemini 11 used the rocket on its Agena target vehicle to raise its apogee to , the highest Earth orbit ever reached by a crewed spacecraft. The perigee was , and maximum velocity (at perigee) was .

If the manoeuvre from GTO to GEO is to be performed with a single impulse, as with a single solid-rocket motor, apogee must occur at an equatorial crossing and at synchronous orbit altitude. This implies an argument of perigee of either 0° or 180°. Because the argument of perigee is slowly perturbed by the oblateness of the Earth, it is usually biased at launch so that it reaches the desired value at the appropriate time (for example, this is usually the sixth apogee on Ariane 5 launchesArianeSpace, Ariane 5 User's Manual Issue 5 Revision 1, 2011 July, p. 2-13, accessed 8 March 2016.).

The film was originally titled The Brain of Frankenstein, but the title was changed during filming to appear like less of a straight horror film and capitalize on Abbott and Costello's marquee value.Furmanek, Bob; Palumbo, Ron (1991). Abbott and Costello in Hollywood. New York: Perigee Books.

"Boogie Woogie Bugle Boy" is a song which became a major hit for The Andrews Sisters and an iconic World War II tune that was written for the Abbott & Costello comedy film, Buck Privates.Furmanek, Bob and Ron Palumbo. "Abbott and Costello in Hollywood." Perigee Books, 1990.

Due to atmospheric drag, the lowest altitude above the Earth at which an object in a circular orbit can complete at least one full revolution without propulsion is approximately 150 km (93 mi) while the lowest perigee of an elliptical revolution is approximately 90 km (56 mi).

As of 29 October 2013, it is in an orbit with a perigee of , an apogee of and 0.14 degrees inclination to the equator. The orbit had a semimajor axis of and eccentricity of 0.0003552, giving it an orbital period of 1,435.75 minutes, or 23.92 hours.

The mission was planned to last 1 hour and 21 minutes, placing the primary payload into its circular orbit at an altitude of about and an inclination of about 69.5 degrees and the secondary payloads into corresponding elliptical orbits with a perigee of about 345 km.

The satellite achieved around two years of operation at that slot before failing in 1969. As of February 4, 2014, Intelsat II F-2 was in an orbit with a perigee of , an apogee of , inclination of 6.80 degrees and an orbital period of 23.93 hours.

Kosmos 31 was placed into a low Earth orbit with a perigee of , an apogee of , 49.0° of inclination, and an orbital period of 91.6 minutes. It decayed from orbit on 20 October 1964. Kosmos 31 was the second of three DS-MT satellites to be launched.

Kosmos 51 was placed into a low Earth orbit with a perigee of , an apogee of , 48.8° of inclination, and an orbital period of 92.5 minutes. It decayed from orbit on 14 November 1965. Kosmos 51 was the last of three DS-MT satellites to be launched.

The satellite separated into an orbit with an apogee of , a perigee of , and 98.3° inclination. It has the International Designator 2009-061A. In total, eight satellites of the Shijian 11 series were launched between 2011 and 2014. They may form a missile warning or SIGINT constellation.

When the craft crosses the equator, the upper stage is fired to raise the spacecraft's apogee to geostationary altitude (and often reduce the inclination of the transfer orbit, as well). Finally, a circularization burn is required to raise the perigee to the same altitude and remove any remaining inclination.

TIROS-9 was launched on January 22, 1965, by a Thor- Delta rocket from Cape Canaveral Air Force Station, Florida. The spacecraft functioned nominally until February 15, 1967. The satellite orbited the Earth once every 2 hours, at an inclination of 96°. Its perigee was and apogee was .

"1960-61 A Bloodless Coup for Macbeth." The Emmys: The Ultimate, Unofficial Guide to the Battle of TV's Best Shows and Greatest Stars. New York: Perigee, 2000. 80. Though traditional comedy and drama series were nominated, the majority of nominees and winners were: telefilms, variety specials, and documentaries.

South Korean science minister Ahn Byung-man later told reporters that the rocket was believed to have exploded. If the launch had been successful, STSAT-2B would have been deployed into an orbit with a perigee of approximately , an apogee of approximately , and around 80 degrees of inclination.

Its perigee was and its apogee was . ESSA-1 had a similar design to that of the TIROS satellite series. It was an 18-sided right prism, measuring across opposite corners and . It had a reinforced baseplate, which carried most of the subsystems and a cover assembly (hat).

IRS-1A was operated in a Sun-synchronous orbit. On 17 March 1988, it had a perigee of , an apogee of , an inclination of 99.01°, and an orbital period of 102.7 minutes. IRS-1A successfully completed its mission in July 1996 after operating for 8 years and 4 months.

Kosmos 106 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 48.4°, and an orbital period of 92.8 minutes. It decayed from orbit on 14 November 1966. Kosmos 106 was the first of nineteen DS-P1-I satellites to be launched.

It was also the first launch from Site 133 at the Plesetsk Cosmodrome. Kosmos 148 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 71.0°, and an orbital period of 91.3 minutes. It decayed from orbit on 7 May 1967.

He created, produced, and was head writer for the original radio and early TV edition of The Life of Riley. He also wrote for Al Jolson on radioKatz, Ephraim (1979). The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books. . P.159.

Comedians Bud Abbott, Lou Costello (not yet a team), Harry Steppe, Joe Penner, Billy Gilbert, Rags Ragland, and Billy Hagan, as well as stripteasers Ann Corio, Hinda Wausau, Gypsy Rose Lee, and Carrie Finnell, performed in Mutual shows.Furmanek, Bob, and Ron Palumbo. "Abbott and Costello in Hollywood." Perigee, 1991.

A total solar eclipse occurred on March 7, 1970, visible across most of North America and Central America. A solar eclipse occurs when the Moon passes between Earth and the Sun, thereby totally or partly obscuring the image of the Sun for a viewer on Earth. A total solar eclipse occurs when the Moon's apparent diameter is larger than the Sun's, blocking all direct sunlight, turning day into darkness. Totality occurs in a narrow path across Earth's surface, with the partial solar eclipse visible over a surrounding region thousands of kilometres wide. Occurring only 1.3 days after perigee (Perigee on March 6, 1970 at 09:32 UTC), the Moon's apparent diameter was very larger.

Occurring only 1 day after perigee (Perigee on April 7, 2024), the Moon's apparent diameter will be larger than usual. With a magnitude of 1.0566, its longest duration of totality will be of four minutes and 28.13 seconds near the town of Nazas, Durango, Mexico, and the nearby city of Torreón, Coahuila. This eclipse will be the first total solar eclipse to be visible from Canada since February 26, 1979, the first in Mexico since July 11, 1991, and the first in the U.S. since August 21, 2017. It will be the only total solar eclipse in the 21st century where totality is visible in Mexico, the United States of America, and Canada.

A total solar eclipse took place on 13–14 November 2012 (UTC). Because it crossed the International Date Line it began in local time on November 14 west of the date line over northern Australia, and ended in local time on November 13 east of the date line near the west coast of South America. Its greatest magnitude was 1.0500, occurring only 12 hours before perigee (Perigee on 2012 Nov 14 at 10:11:48 UTC), with greatest eclipse totality lasting just over four minutes. A solar eclipse occurs when the Moon passes between Earth and the Sun, thereby totally or partly obscuring the image of the Sun for a viewer on Earth.

Sky and Telescope magazine chose a definition of . TimeandDate.com prefers a definition of . EarthSky uses Nolle's definition comparing their calculations to tables published by Nolle in 2000. Wood also coined the less used term proxigee where perigee and the full or new moon are separated by 10 hours or less.

TIROS-10 was launched on July 2, 1965, by a Thor-Delta rocket from Cape Canaveral Air Force Station, Florida, United States. The spacecraft functioned nominally until July 31, 1966. The satellite orbited the Earth once every 100 minutes, at an inclination of 98°. Its perigee was and apogee was .

TIROS 4 was launched on February 8, 1962, by a Thor- Delta rocket from Cape Canaveral Air Force Station, Florida. The spacecraft functioned nominally until June 30, 1962. The satellite orbited the Earth once every 1 hour and 30 minutes, at an inclination of 48.3°. Its perigee was and apogee was .

Nimbus 4 was launched on April 8, 1970, by a Thor-Agena rocket from Vandenberg Air Force Base, Lompoc, CA. The spacecraft functioned nominally until 30 Sep 1980. The satellite orbited the Earth once every 1 hour and 47 minutes, at an inclination of 80°. Its perigee was and apogee was .

Nimbus 3 was launched on April 14, 1969, by a Thor-Agena rocket from Vandenberg Air Force Base, Lompoc, CA. The spacecraft functioned nominally until 22 January 1972. The satellite orbited the Earth once every 1 hour and 47 minutes, at an inclination of 99.9°. Its perigee was and apogee was .

The launch placed Skynet 5B into a geosynchronous transfer orbit with 6 degrees of inclination. The satellite used its apogee motor to raise itself into geostationary orbit. It is located at a longitude of 53° East, in an orbit with a perigee of , an apogee of , and 0 degrees inclination.

Nimbus 7 was launched on October 24, 1978, by a Delta rocket from Vandenberg Air Force Base, California, United States. The spacecraft functioned nominally until 1994. The satellite orbited the Earth once every 1 hour and 34 minutes, at an inclination of 99 degrees. Its perigee was and apogee was .

Alice White (born Alva White, August 25, 1904The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume incorrectly lists White's date of birth as August 28, 1907.Katz, Ephraim (1979). The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books.

Relay 2 was launched atop a Delta B rocket on January 21, 1964 from LC-17B at Cape Canaveral Air Force Station. Apogee 7600 km; perigee 1870 km. It was physically similar to Relay 1. Design changes in this satellite improved its performance so response to spurious commands was essentially eliminated.

Isolated hairs can be removed with tweezers or electrolysis. Discomfort following the procedure generally lasts two to five days or less.Hilda Hutcherson, Pleasure, page 190, Perigee, 2006, Application of egg oil for a few days post-waxing can help moisturize the skin and reduce inflammation, pain or growth of bacteria.

The spacecraft reentered on 25 June 1967. It was deployed into a low Earth orbit with a perigee of , an apogee of , an inclination of 51.8° to the equator, and orbital period of 89.2 minutes. It would have received the next designation in the Venera series, at the time Venera 5.

Totality occurs in a narrow path across Earth's surface, with the partial solar eclipse visible over a surrounding region thousands of kilometres wide. Occurring 2.2 days before perigee (June 23, 2001), the Moon's apparent diameter was larger. This solar eclipse occurred 11 days after the 2001 FIFA Confederations Cup Final.

IRS-1B was operated in a Sun-synchronous orbit. On 29 August 1991, it had a perigee of , an apogee of , an inclination of 99.2°, and an orbital period of 102.7 minutes. IRS-1B successfully completed its mission on 20 December 2003, after operating for 12 years and 4 months.

Following the launch of CBERS-2B in 2007, CBERS-2 was retired from service. As of 1 December 2013, the dericict satellite remains in orbit, with a perigee of , an apogee of , 98.17 degrees inclination and a period of 100.33 minutes. Its orbit has a semimajor axis of , and eccentricity of 0.0001886.

The mission was planned to last 1 hour, 45 minutes and 33 seconds from lift-off until separation, placing its payload into a low Earth parking orbit with a perigee of about , an apogee of about , and an inclination of about 5.96°, from which the spacecraft autonomously reached its L1 Lissajous orbit.

TIROS 5 was launched on June 19, 1962, by a Thor- Delta rocket from Cape Canaveral Air Force Station, Florida, United States. The spacecraft functioned nominally until June 30, 1962. The satellite orbited the Earth once every 1 hour and 30 minutes, at an inclination of 58°. Its perigee was and apogee was .

TIROS 6 was launched on September 18, 1962, by a Thor-Delta rocket from Cape Canaveral Air Force Station, Florida, United States. The spacecraft functioned nominally until October 21, 1962. The satellite orbited the Earth once every 1 hour and 38 minutes, at an inclination of 58.3°. Its perigee was and apogee was .

Upon successfully reaching orbit, it was assigned the Harvard designation 1961 Alpha Kappa 1. OSCAR 1, the first amateur radio satellite, was launched aboard the same rocket. Discoverer 36 was operated in a low Earth orbit, with a perigee of , an apogee of , 81.1 degrees of inclination, and a period of 91.2 minutes.

On 14 June 1993, USA-91 was in an orbit with a perigee of , an apogee of , a period of 717.88 minutes, and 54.9 degrees of inclination to the equator. It broadcast signal PRN 07, and operated in slot 4 of plane C of the GPS constellation. The satellite had a mass of .

Approximately nine minutes following the liftoff, the Progress M-13M spacecraft successfully reached orbit and deployed its solar arrays and navigation antennas. The spacecraft was inserted into a parking low-Earth orbit with 51.65° of orbital inclination, perigee of 192.98 km minimal altitude, apogee of 252.9 km maximum altitude, 88.66 minutes orbital period.

Because a satellite in an eccentric orbit moves faster near perigee and slower near apogee, it is possible for a satellite to track eastward during part of its orbit and westward during another part. This phenomenon allows for ground tracks which cross over themselves, as in the geosynchronous and Molniya orbits discussed below.

New York: Perigee Books. The film was not released until August 1959, five months after Costello died of a heart attack. Much of the outdoor footage was shot at the Iverson Movie Ranch in Chatsworth, Calif., including a number of scenes depicting the oversized blonde beauty at her new home—a barn.

However, it is more fuel-efficient for a craft to burn its fuel as close to the ground as possible; see Oberth effect and reference.Escape Velocity of Earth. Van.physics.uiuc.edu. Retrieved on 2011-10-05. This is another way to explain the performance penalty associated with establishing the safe perigee of a parking orbit.

Kosmos 23 was the second of two Omega satellites to be launched, after Kosmos 14. It was operated in an orbit with a perigee of , an apogee of , an inclination, and an orbital period of 92.3 minutes. It remained in orbit until it decayed and reentered the atmosphere on 27 March 1964.

Kosmos 356 was the second of two DS-U2-MG satellites to be launched, after Kosmos 321. It was operated in an orbit with a perigee of , an apogee of , 81.9 degrees of inclination, and an orbital period of 92.3 minutes, before decaying from orbit and reentering the atmosphere on 2 October 1970.

The satellite remains in orbit; as of it was in an orbit with a perigee of , an apogee of and inclination of degrees. This near-earth elliptical orbit was 114.09 minutes per orbit. It has Satellite Catalog Number 4382 and International Designator 1970-034A. Dongfanghong I had a design life of 20 days.

Amateur observations have located the spacecraft in an orbit with a perigee of and an apogee of , inclined at 64.4 degrees to the plane of the equator. Current generation NOSS satellites are always launched and operated in pairs, and are used to locate and track ships from the radio transmissions that they emit.

New York City: Perigee (Penguin Group) 2008, In fiction, a character in Sir Arthur Conan Doyle's The Red-Headed League is hired to copy out the Britannica by hand—for no other reason (at least apparently) than his red hair—although his job is terminated before he finishes the entries beginning with "A".

But the orbit analysis had failed to take into consideration the influence of the Moon at such high apogees and the perigee started to drop dangerously fast. Most of its propellant had to be spent and the solar panels suffered damage that reduced the power production. It was never commissioned into service.

Kosmos 335 was one of the DS-U1-R satellites. It was operated in an orbit with a perigee of , an apogee of , 48.4 degrees of inclination, and an orbital period of 90.9 minutes. It completed operations on 20 June 1970. On 22 June 1970, it decayed from orbit and reentered the atmosphere.

Tests have started to be effectively performed by using the LAGEOS and LAGEOS II satellites in 1996, according to a strategy involving the use of a suitable combination of the nodes of both satellites and the perigee of LAGEOS II. The latest tests with the LAGEOS satellites have been performed in 2004–2006 by discarding the perigee of LAGEOS II and using a linear combination. Recently, a comprehensive overview of the attempts to measure the Lense-Thirring effect with artificial satellites was published in the literature. The overall accuracy reached in the tests with the LAGEOS satellites is subject to some controversy. The Gravity Probe B experimentEveritt, C. W. F, The Gyroscope Experiment I. General Description and Analysis of Gyroscope Performance.

CBERS-1 was decommissioned in September 2003, almost four years after launch. The derelict satellite remains in orbit; as of 30 November 2013 it is in an orbit with a perigee of , an apogee of , 98.34 degrees inclination and a period of 100.35 minutes. The orbit has a semimajor axis of , and eccentricity of 0.0004025.

ASTRO was a spacecraft, which was built by Boeing. It was operated in low Earth orbit. On 9 March 2007, it had a perigee of , an apogee of , 46.0 degrees of inclination, and an orbital period of 94.49 minutes. After completing operations, the ASTRO and NEXTSat spacecraft were separated, and ASTRO performed a separation burn.

The satellite was deployed into a low Earth orbit with a perigee of 224 km, an apogee of 470 km, an inclination of 55.53°, and an orbital period of 91.5 minutes. Fajr reentered in the Earth's atmosphere on 26 February 2015 after 23.8 days in orbit. Apparently, it performed no maneuvers during its orbital lifetime.

Kosmos 378 was the only DS-U2-IP satellite to be launched. It was operated in an orbit with a perigee of , an apogee of , 74 degrees of inclination, and an orbital period of 104.4 minutes. It completed operations on 13 September 1971, before decaying from orbit and reentering the atmosphere on 17 August 1972.

In February 1967, the backup booster and spacecraft were set up at LC-1 and the planned mission could be carried out. Kosmos 140 was operated in a low Earth orbit, on 7 February 1967, it had a perigee of , an apogee of , an inclination of 51.7°, and an orbital period of 88.5 minutes.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1968-043A. Kosmos 221 was operated in an orbit with a perigee of , an apogee of , an inclination of 48.4°, and an orbital period of 108.3 minutes. It remained in orbit until it decayed and reentered the atmosphere on 31 August 1969.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1968-044A. Kosmos 222 was operated in an orbit with a perigee of , an apogee of , an inclination of 71.0°, and an orbital period of 92.3 minutes. It remained in orbit until it decayed and reentered the atmosphere on 11 October 1968.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1968-028A. Kosmos 211 was operated in an orbit with a perigee of , an apogee of , an inclination of 81.9°, and an orbital period of 102.5 minutes. It remained in orbit until it decayed and reentered the atmosphere on 10 November 1968.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1968-061A. Kosmos 233 was operated in an orbit with a perigee of , an apogee of , an inclination of 82.0°, and an orbital period of 102.1 minutes. It remained in orbit until it decayed and reentered the atmosphere on 7 February 1969.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1968-083A. Kosmos 245 was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.6 minutes. It remained in orbit until it decayed and reentered the atmosphere on 15 January 1969.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1968-107A. Kosmos 257 was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.10 minutes. It remained in orbit until it decayed and reentered the atmosphere on 5 March 1969.

Due to atmospheric drag, the lowest altitude at which an object in a circular orbit can complete at least one full revolution without propulsion is approximately . The expression "orbital spaceflight" is mostly used to distinguish from sub-orbital spaceflights, which are flights where the apogee of a spacecraft reaches space, but the perigee is too low.

On 19 April 1975, the satellite's 96.46-minute orbit had an apogee of and a perigee of , at an inclination of 50.7 degrees. It was built to conduct experiments in X-ray astronomy, aeronomics, and solar physics. The spacecraft was a 26-sided polyhedron in diameter. All faces (except the top and bottom) were covered with solar cells.

Abbott and Costello in Hollywood. New York: Perigee Books. A bit part in the film went to the "just released from contract" Mouseketeer Sherry Allen, who was advised by Lou Costello to return to the use (professionally) of her true surname, "Alberoni". She took his advice, and has been known professionally since that time by her birth name.

Explorer 50 was launched on 23 October 1973 at 02:26:03 UTC, by a Delta 1604 rocket from Cape Canaveral AFS, Florida. The spacecraft functioned nominally until 7 October 2006. The satellite orbited the Earth once every 12 days, at an inclination of 28.6 degrees. Its perigee was 22 earth radii and apogee was 45 earth radii.

New York: Perigee Books. Although Abbott and Costello were called "Pete Patterson" and "Freddie Franklin" in the script and in the closing credits, they used their real names onscreen during filming. In Universal's previous Mummy films, the Mummy was called "Kharis", but in this film it is called "Klaris." Stuntman Eddie Parker (billed as "Edwin") played the mummy.

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 31 October 1990, USA-64 was in an orbit with a perigee of , an apogee of , a period of 717.94 minutes, and 54.9 degrees of inclination to the equator. It operated in slot 5 of plane D of the GPS constellation.

New York: Perigee Books. The Ink Spots performed in this movie and were portrayed as waiters. "Do I Worry?" was a feature for lead tenor Bill Kenny and 2nd tenor Deek Watson was featured on "Shout Brother Shout" singing the lead part and playing trumpet. The famous dance group "Tip, Tap, and Toe" danced during the nightclub scene.

Elektron 2's orbit took the spacecraft beyond the Earth's magnetosphere to penetrate the shock wave and turbulent area marking the Earth's magnetopause: its initial perigee was , the apogee was , its orbital inclination was 61°, and its period 1,360 minutes. Elektron 1 returned usable data as late as October 1964; Elektron 2 as late as May 1964.

The lunar distance is approximately 400,000 km, or a quarter of a million miles. The mean semi-major axis has a value of . The time-averaged distance between Earth and Moon centers is . The actual distance varies over the course of the orbit of the Moon, from at the perigee to at apogee, resulting in a differential range of .

Kosmos 348 was the second of two DS-U2-GK satellites to be launched. It was operated in an orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 92.4 minutes. It decayed from orbit within a few weeks of its launch, reentering the atmosphere on 25 July 1970.

Abbott and Costello in Hollywood. New York: Perigee Books. Universal then put Oh, Charlie back into production in mid-May to append the opening and closing of the film with musical numbers by the Andrews Sisters (who appeared in both service comedies) and bandleader Ted Lewis. New scenes were written and others were re-shot for continuity purposes.

However without the perigee motor the satellite could not be boosted to its nominal geostationary orbit. The on- board propulsion system was used to move the satellite into a slightly higher stable orbit. Intelsat arranged for a rescue of 603 by the US Space Shuttle. STS-49 was launched on May 7, 1992, 7:40 p.m. EDT.

After a six and a half hour mission, the DM-3SLB successfully separated the spacecraft and at 03:28 UTC, first signals from spacecraft were received. The launch put the satellite with margins of its planned geosynchronous transfer orbit with a perigee of 10,286 km, an apogee of 35,790 km and a 12° inclination to the Equator.

The United Launch Alliance was contracted to launch TDRS-12. The spacecraft was launched on 24 January 2014 at 02:33 UTC (21:33 local time on 23 January). An Atlas V rocket was used, flying in the 401 configuration, with tail number AV-043. After launch, TDRS-12 was deployed into a high-perigee geosynchronous transfer orbit.

Abbott and Costello in Hollywood. New York: Perigee Books. The role eventually played by Boris Karloff in the film was originally a female character named Madame Switzer in the final shooting script which was then titled, Abbott and Costello Meet the Killers. Five days before shooting, Karloff was hired and the character was changed to a swami.

Kosmos 440 was placed into a low Earth orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 95.2 minutes. It decayed from orbit on 29 October 1972. Kosmos 440 was the eleventh of nineteen DS-P1-I satellites to be launched. Of these, all reached orbit successfully except the seventh.

Kosmos 497 was placed into a low Earth orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 95.2 minutes. It decayed from orbit on 7 November 1973. Kosmos 497 was the twelfth of nineteen DS-P1-I satellites to be launched. Of these, all reached orbit successfully except the seventh.

Kosmos 615 was placed into a low Earth orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 95.7 minutes. It decayed from orbit on 17 December 1975. Kosmos 615 was the thirteenth of nineteen DS-P1-I satellites to be launched. Of these, all reached orbit successfully except the seventh.

Kosmos 662 was placed into a low Earth orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 95.5 minutes. It decayed from orbit on 28 August 1976. Kosmos 662 was the fourteenth of nineteen DS-P1-I satellites to be launched. Of these, all reached orbit successfully except the seventh.

Kosmos 750 was placed into a low Earth orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 95.4 minutes. It decayed from orbit on 29 September 1977. Kosmos 750 was the fifteenth of nineteen DS-P1-I satellites to be launched. Of these, all reached orbit successfully except the seventh.

Kosmos 801 was placed into a low Earth orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 95.3 minutes. It decayed from orbit on 5 January 1978. Kosmos 801 was the sixteenth of nineteen DS-P1-I satellites to be launched. Of these, all reached orbit successfully except the seventh.

Kosmos 849 was placed into a low Earth orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 96 minutes. It decayed from orbit on 24 April 1978. Kosmos 849 was the seventeenth of nineteen DS-P1-I satellites to be launched. Of these, all reached orbit successfully except the seventh.

Kosmos 901 was placed into a low Earth orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 95.5 minutes. It decayed from orbit on 28 June 1978. Kosmos 901 was the eighteenth of nineteen DS-P1-I satellites to be launched. Of these, all reached orbit successfully except the seventh.

Kosmos 362 was placed into a low Earth orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 95.6 minutes. It decayed from orbit on 13 October 1971. Kosmos 362 was the ninth of nineteen DS-P1-I satellites to be launched. Of these, all reached orbit successfully except the seventh.

Kosmos 391 was placed into a low Earth orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 95.3 minutes. It decayed from orbit on 21 February 1971. Kosmos 391 was the tenth of nineteen DS-P1-I satellites to be launched. Of these, all reached orbit successfully except the seventh.

Kosmos 275 was placed into a low Earth orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 95.2 minutes. It decayed from orbit on 7 February 1970. Kosmos 275 was the fifth of nineteen DS-P1-I satellites to be launched. Of these, all reached orbit successfully except the seventh.

Kosmos 327 was placed into a low Earth orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 95.7 minutes. It decayed from orbit on 19 January 1971. Kosmos 327 was the eighth of nineteen DS-P1-I satellites to be launched. Of these, all reached orbit successfully except the seventh.

Kosmos 242 was placed into a low Earth orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 91.3 minutes. It decayed from orbit on 13 November 1968. Kosmos 242 was the fourth of nineteen DS-P1-I satellites to be launched. Of these, all reached orbit successfully except the seventh.

The launch occurred at 10:07 GMT on 21 March 1967. Kosmos 149 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 48.4°, and an orbital period of 89.76 minutes. It decayed from orbit on 7 April 1967. Kosmos 149 was the first of two DS-MO satellites to be launched.

Kosmos 53 was placed into a low Earth orbit with a perigee of , an apogee of , 48.8° of inclination, and an orbital period of 98.7 minutes. It decayed on 12 August 1966. Kosmos 53 was the fifth of seven DS-A1 satellites to be launched, and the third to reach orbit after Kosmos 11 and Kosmos 17.

Kosmos 11 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 49.0°, and an orbital period of 96.1 minutes. It decayed on 18 May 1964. Kosmos 11 was the first of seven DS-A1 satellites to be launched. The next DS-A1 launched will be Kosmos 17, on 22 May 1963.

BeeSat-1 was a secondary payload aboard the rocket, which deployed the Oceansat-2 satellite. Five other secondary payloads were flown aboard the rocket; SwissCube-1, UWE-2, ITU-pSat1, Rubin 9.1 and Rubin 9.2. BeeSat-1 is operating in a sun synchronous orbit with an apogee of , a perigee of and 98.4 degrees of inclination to the equator.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1967-115A. Kosmos 191 was operated in an orbit with a perigee of , an apogee of , an inclination of 71.0°, and an orbital period of 92.2 minutes. It was a spacecraft. It remained in orbit until it decayed and reentered the atmosphere on 2 March 1968.

Kosmos 98 was operated in a low Earth orbit, at an epoch of 27 November 1965, it had a perigee of , an apogee of , an inclination of 65.0° and an orbital period of 92.0 minutes. On 5 December 1965, after eight days in orbit, the satellite was deorbited with its return capsule descending by parachute for recovery by the Soviet Force.

Kosmos 105 was operated in a low Earth orbit; at an epoch of 22 January 1966 it had a perigee of , an apogee of , an inclination of 65.0° and an orbital period of 89.7 minutes. On 30 January 1966, after eight days in orbit, the satellite was deorbited with its return capsule descending by parachute for recovery by Soviet force.

The term supermoon is attributed to astrologer Richard Nolle while reading “Strategic Role Of Perigean Spring Tides in Nautical History and Coastal Flooding” published in 1976 by NOAA Hydrologist Fergus Wood. In practice, there is no official or even consistent definition of how near perigee the full Moon must occur to receive the supermoon label, and new moons rarely receive a supermoon label.

Scientists have confirmed that the combined effect of the Sun and Moon on the Earth's oceans, the tide, is greatest when the Moon is either new or full. and that during lunar perigee, the tidal force is somewhat stronger, resulting in perigean spring tides. However, even at its most powerful, this force is still relatively weak, causing tidal differences of inches at most.

ESSA-4 was launched on January 26, 1967 at 17:31 UTC. It was launched atop a Delta rocket from Vandenberg Air Force Base, California, U.S.. The spacecraft had a mass of at the time of launch. ESSA-4 had an inclination of 102°, and an orbited the earth once every 113.4 minutes. Its perigee was and its apogee was .

ESSA-5 was launched on April 20, 1967 at 11:17 UTC. It was launched atop a Delta rocket from Vandenberg Air Force Base, California, U.S.. The spacecraft had a mass of at the time of launch. ESSA-5 had an inclination of 101.9°, and an orbited the earth once every 113.6 minutes. Its perigee was and its apogee was .

Kosmos 101 separated from its carrier rocket into a low Earth orbit with a perigee of , an apogee of , an inclination of 49.0°, and an orbital period of 92.4 minutes. It decayed from orbit on 12 July 1966. Kosmos 101 was the fourth of seventy nine DS-P1-Yu satellites to be launched, of which all but seven were successful.

Kosmos 116 separated from its carrier rocket into a low Earth orbit with a perigee of , an apogee of , an inclination of 48.4°, and an orbital period of 92.0 minutes. It decayed from orbit on 3 December 1966. Kosmos 116 was the fifth of seventy nine DS-P1-Yu satellites to be launched, and the fourth of seventy two to successfully reach orbit.

Kosmos 152 separated from its carrier rocket into a low Earth orbit with a perigee of , an apogee of , an inclination of 71.0°, and an orbital period of 92.2 minutes. It decayed from orbit on 5 August 1967. Kosmos 152 was the seventh of seventy nine DS-P1-Yu satellites to be launched, and the sixth of seventy two to successfully reach orbit.

Kosmos 165 separated from its carrier rocket into a low Earth orbit with a perigee of , an apogee of , an inclination of 81.9°, and an orbital period of 102.1 minutes. It decayed from orbit on 15 January 1968. Kosmos 165 was the eighth of seventy nine DS-P1-Yu satellites to be launched, and the seventh of seventy two to successfully reach orbit.

After separating from its carrier rocket, Kosmos 36 was in a low Earth orbit with a perigee of , an apogee of , 49.0° of inclination, and an orbital period of 91.9 minutes. It decayed from orbit on 28 February 1965. Kosmos 36 was the first of seventy nine DS-P1-Yu satellites to be launched, of which all but seven were successful.

The launch occurred from Site 43/4 at the Plesetsk Cosmodrome at 00:58:39 GMT on 2 November 2010. It was constructed by ISS Reshetnev and is believed to be based on the Uragan-M satellite bus, which has also been used for GLONASS navigation satellites. It operates in a Molniya orbit with a perigee of , an apogee of , and 65° inclination.

Brian Burger, "NASA's Terra Satellite Moved to Avoid Chinese ASAT Debris" , space.com. Retrieved 6 July 2007. On 20 February 2008, the U.S. launched an SM-3 missile from the USS Lake Erie to destroy a defective U.S. spy satellite thought to be carrying of toxic hydrazine propellant. The event occurred at about , and the resulting debris has a perigee of or lower.

By 8 November 1978, OPS 5113 was in an orbit with a perigee of , an apogee of , a period of 718.02 minutes, and 62.8 degrees of inclination to the equator. The satellite had a design life of 5 years and a mass of . It broadcast the PRN 06 signal in the GPS demonstration constellation, and was retired from service on 18 May 1992.

On the other hand, the Yippies employed theatrical gestures, such as advancing a pig ("Pigasus the Immortal") as a candidate for President in 1968, to mock the social status quo. They have been described as a highly theatrical, anti- authoritarian and anarchistAbbie Hoffman, Soon to be a Major Motion Picture, p. 128. Perigee Books, 1980. youth movement of "symbolic politics".

Kosmos 154 was launched using a Proton-K carrier rocket, which flew from Site 81/23 at Baikonur. The launch occurred at 09:07 GMT on 8 April 1967. Kosmos 154 was operated in an Earth orbit, it had a perigee of , an apogee of , an inclination of 51.6° and an orbital period of 88.5 minutes. Kosmos 154 had a mass of .

The 4 SkySats, numbered 4 to 7, with individual masses of approximately , were in the upper position. Their target orbit was a sun-synchronous orbit with a semi-major axis of (perigee of and apogee of ) and an inclination of 97.4°. They were deployed one by one every 2 seconds starting approximately 40 minutes and 21 seconds after lift-off.

The launch of TIROS-2 Universal newsreel about TIROS-2 TIROS 2 was launched on November 23, 1960 at 11:13:03 UTC, by a Thor-Delta rocket from Cape Canaveral, Florida. The spacecraft functioned nominally until January 22, 1962. The satellite orbited the Earth once every 98 minutes, at an inclination of 48.5°. Its perigee was and apogee was .

INSAT-4B was successfully inserted into geosynchronous transfer orbit, from which it raised itself into geostationary orbit using a liquid-fuelled apogee motor. It received the International Designator 2007-007A and Satellite Catalog Number 30793. As of 11 November 2013, it is in an orbit with a perigee of , an apogee of , inclination of 0.07 degrees and an orbital period of 23.93 hours.

It is in a Molniya orbit with a perigee of , an apogee of , and 63.2° of inclination. In addition to its SIGINT payload, USA-184 also carries two secondary instruments; the SBIRS- HEO-1 missile detection payload as part of the Space-Based Infrared System programme, and NASA's TWINS-1 or TWINS-A magnetospheric science instrument as part of the TWINS programme.

Similar orbits with an argument of perigee of 90° could allow high-latitude coverage in the southern hemisphere. A proposed constellation, the Antarctic Broadband Program, would have used satellites in an inverted Molniya orbit to provide broadband internet service to facilities in Antarctica. Initially funded by the now defunct Australian Space Research Program, it did not progress beyond initial development.

Animation of Jason-3 orbit from 20 May 2018 to 14 November 2018. Earth is not shown. Jason-3 flies at the same 9.9-day repeat track orbit and this means the satellite will make observations over the same ocean point every 9.9 days. The orbital parameters are: 66.05º inclination, 1380 km apogee, 1328 km perigee, 112 minutes per revolution around Earth.

Katz, Ephraim (1979). The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume, Perigee Books; , pg. 359. Moving to Hollywood in an attempt to become a star, she was discovered while working at an ice cream parlor where one of the customers, actor William Demarest, took notice of her and eventually helped her get into films.

Early Zenits were launched using the Vostok rocket; later versions used the Voskhod and the Soyuz rockets. The first flights were launched from Baikonur Cosmodrome but subsequent launches also took place at Plesetsk Cosmodrome. Most Zenits flew in a slightly elliptical orbit with a perigee of around and an apogee between ; the missions usually lasted between 8 and 15 days.

Kosmos 14 was the first of two Omega satellites to be launched, the other being Kosmos 23. It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.88°, and an orbital period of 91.3 minutes. It remained in orbit until it decayed and reentered the atmosphere on 29 August 1963 after 138 days in orbit.

Kosmos 321 was the first of two DS-U2-MG satellites to be launched, the other being Kosmos 356. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.3 minutes. It completed operations on 13 March 1970, before decaying from orbit and reentering the atmosphere on 23 March.

Pegasus 2 was operated in a low Earth orbit. On 3 July 1965 it was catalogued as being in an orbit with a perigee of and an apogee of , inclined at 31.7 degrees to the equator and with a period of 97.15 minutes. Once in orbit, the panels were deployed to detect micrometeoroid impacts. Experiment results were returned to Earth by radio.

Pegasus 3 was operated in a low Earth orbit. On 3 September 1965 it was catalogued as being in an orbit with a perigee of and an apogee of , inclined at 51.6 degrees to the equator and with a period of 95.15 minutes. Once in orbit, the panels were deployed to detect micrometeoroid impacts. Experiment results were returned to Earth by radio.

Pegasus 1 was operated in a low Earth orbit. On 18 March 1965 it was catalogued as being in an orbit with a perigee of and an apogee of , inclined at 31.7 degrees to the Equator and with a period of 97.00 minutes. Once in orbit, the panels were deployed to detect micrometeoroid impacts. Experiment results were returned to Earth by radio.

The Space Archive The spacecraft was placed in an orbit with a perigee of and an apogee of . After reaching orbit, its telescoping boom was extended outward by . Two star cameras were used to define the position of the spacecraft relative to Earth. The orbit allowed the satellite to map a majority of the Earth's surfaces except the geographic poles.

C/NOFS had a three-axis stabilisation system, and was equipped with seven sensors. It was placed into a low Earth orbit with orbital inclination of 13°, a perigee of 400 km and an apogee of 850 km. It carried the CINDI experiment for NASA. Launch was originally scheduled for 2003, but was delayed due to a number of issues.

It is in a Molniya orbit with a perigee of , an apogee of , and 63.5° of inclination. In addition to its SIGINT payload, USA-200 also carries two secondary instruments; the SBIRS- HEO-2 missile detection payload as part of the Space-Based Infrared System programme, and NASA's TWINS-2 or TWINS-B magnetospheric science instrument as part of the TWINS programme.

It was launched aboard a Kosmos-2I 63SM rocket, from Site 133/1 at Plesetsk. The launch occurred at 11:59:59 UTC on 4 November 1969. Kosmos 308 was placed into a low Earth orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 91.3 minutes. It decayed from orbit on 4 January 1970.

The launch occurred at 20:18:59 UTC on 29 September 1972. Kosmos 521 was placed into a low Earth orbit with a perigee of , an apogee of , 65.8 degrees of inclination, and an orbital period of 104.9 minutes. No attempt to intercept the satellite was made after its onboard telemetry system malfunctioned. As of 2009, it is still in orbit.

The launch occurred at 18:28:00 GMT on 5 March 1968. Kosmos 204 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 70.0°, and an orbital period of 95.9 minutes. It decayed from orbit on 2 March 1969. Kosmos 204 was the third of nineteen DS-P1-I satellites to be launched.

Kosmos 320 was placed into a low Earth orbit with a perigee of , an apogee of , 48.4 degrees of inclination, and an orbital period of 90.2 minutes. It decayed from orbit on 10 February 1970. Kosmos 320 was the second of two DS-MO satellites to be launched. It was preceded by Kosmos 149, which was launched in March 1967.

In September 2011 a team at University College London's Mullard Space Science Laboratory announced plans to re-establish communications with Prospero, in time for the satellite's 40th anniversary. As of September 2012, not much progress had been made in establishing contact with the satellite due to time constraints. At perigee, Prospero can be seen through binoculars at magnitude +6 overhead, steady.

Kosmos 70 was placed into a low Earth orbit with a perigee of , an apogee of , an 48.8° of inclination, and an orbital period of 98.3 minutes. It decayed on 18 December 1966. Kosmos 70 was the last of seven DS-A1 satellites to be launched, of which four; Kosmos 11, Kosmos 17, Kosmos 53 and Kosmos 70, reached orbit.

It was launched aboard a Kosmos-2I 63S1 rocket, from Mayak-2 at Kapustin Yar. The launch occurred at 06:00:00 GMT on 6 August 1963. Kosmos 19 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 49.0°, and an orbital period of 92.2 minutes. It decayed from orbit on 30 March 1964.

Kosmos 68 was operated in a low Earth orbit; at an epoch of 17 June 1965 it had a perigee of , an apogee of , an inclination of 65.0° and an orbital period of 89.8 minutes. On 23 June 1965, after eight days in orbit, the satellite was deorbited with its return capsule descending by parachute for recovery by Soviet forces.

Kosmos 78 was operated in a low Earth orbit; at an epoch of 14 August 1965, it had a perigee of , an apogee of , an inclination of 69.0° and an orbital period of 89.9 minutes. On 22 August 1965, after eight days of operation the satellite was deorbited, with its return capsule descending by parachute for recovery by Soviet force.

The origin of the word is an evolution of the term Yippie, which was coined by the Youth International Party in the 1960s. After these events, "the Zippies evolved back into Yippies",Abbie Hoffman, Soon to be a Major Motion Picture, page 278. Perigee Books, 1980. but the word Zippie remained, used by record labels, rock bands, and assorted others.

Five other secondary payloads were flown aboard the rocket; BeeSat, UWE-2, ITU-pSat1, Rubin 9.1 and Rubin 9.2. SwissCube-1 is operating in a sun synchronous orbit with an apogee of , a perigee of and 98.28 degrees of inclination to the equator. It has an orbital period of 98.5 minutes. Its mission was expected to last between three and twelve months.

Hisaki carries an extreme ultraviolet spectrometer which will be used to study the composition of the atmospheres and the behavior of the magnetospheres of the planets of the Solar System. Designed for a one-year mission, Hisaki will be operated in a low Earth orbit with a perigee of , an apogee of , 31 degrees of inclination and a period of 106 minutes.

Totality occurs in a narrow path across Earth's surface, with the partial solar eclipse visible over a surrounding region thousands of kilometres wide. Annularity was first visible from southeastern tip of Venezuela, northern tip of Brazil, British Guyana (today's Guyana), Dutch Guiana (today's Suriname) and Porto Santo Island in Madeira, Portugal, then totality from Portugal and Spain, with annularity continued northeast across France (including northwestern suburbs of Paris), Belgium, Netherlands, Germany and Russian Empire (the parts now belonging to northern Latvia, southern Estonia and Russia). Occurring 7.4 days after apogee (Apogee on April 10, 1912) and only 5.5 days before perigee (Perigee on April 22, 1912), the Moon's apparent diameter was larger. It was the 30th eclipse of the 137th Saros cycle, which began with a partial eclipse on May 25, 1389 and will conclude with a partial eclipse on June 28, 2633.

Annularity was visible from Car Nicobar, the northernmost of the Nicobar Islands, and Burma, Thailand including Bangkok, French Indochina (the part now belonging to Laos), North Vietnam (now belonging to Vietnam), China, South Korea, Rebun Island in Japan, Kuril Islands in the Soviet Union (now belonging to Russia) on May 9th, and Alaska on May 8th. It was the first central solar eclipse visible from Bangkok from 1948 to 1958, where it is rare for a large city to witness 4 central solar eclipses in just 9.945 years. The moon’s apparent diameter was only 0.006% smaller than the Sun’s, so this was an annular solar eclipse that occurred on May 9, 1948. Occurring 7.1 days after apogee (Apogee on May 2, 1948) and 6.6 days before perigee (Perigee on May 15, 1948), the Moon's apparent diameter was near the average diameter.

On 27 October 1967 at 09:29:59 GMT, the Soyuz 11A511 s/n U15000-05 booster and Kosmos 186 were set up at Site 31/6 of Baikonur Cosmodrome and the planned mission could be carried out. Kosmos 186 was operated in a low Earth orbit, it had a perigee of , an apogee of , an inclination of 51.7°, and an orbital period of 88.7 minutes, and had a mass of . On 30 October 1967 at 08:12:41 GMT, the Soyuz 11A511 s/n N15000-07 booster and Kosmos 188 were set up at Site 1/5 of Baikonur Cosmodrome and the planned mission could be carried out. Kosmos 188 was operated in a low Earth orbit, it had a perigee of , an apogee of , an inclination of 51.7°, and an orbital period of 89.0 minutes, and had a mass of .

Unable to achieve orbit, the rocket and payloads fell into the Pacific Ocean. NanoSail-D was to have been operated in a low Earth orbit with a perigee of , an apogee of and 9 degrees of inclination. It would have been operational for around seven days, after which time it would have been expected to run out of power. Its solar sail had an area of .

Kosmos 124 was operated in a low Earth orbit, at an epoch of 14 July 1966, it had a perigee of , an apogee of , an inclination of 51.8°, and an orbital period of 89.4 minutes. After eight days in orbit, Kosmos 124 was deorbited, with its return capsule descending under parachute, landing at 09:22 GMT on 22 July 1966, and recovered by Soviet force.

Kosmos 107 was operated in a low Earth orbit, at an epoch of 10 February 1966, it had a perigee of , an apogee of , an inclination of 65.0° and an orbital period of 89.7 minutes. After eight days in orbit, Kosmos 107 was deorbited, with its return capsule descending under parachute, landing at 06:29 GMT on 18 February 1966, and recovered by Soviet force.

Kosmos 112 was operated in a low Earth orbit, at an epoch of 17 March 1966, it had a perigee of , an apogee of , an inclination of 72.0° and an orbital period of 92.1 minutes. After eight days in orbit, Kosmos 112 was deorbited, with its return capsule descending under parachute and landing at 05:31 GMT on 25 March 1966 et recovered by Soviet force.

Kosmos 117 was operated in a low Earth orbit, at an epoch of 6 May 1966, it had a perigee of , an apogee of , an inclination of 65.0°, and an orbital period of 89.5 minutes. After eight days in orbit, Kosmos 117 was deorbited, with its return capsule descending under parachute and landing at 08:24 GMT on 14 May 1966 and recovered by Soviet force.

Kosmos 129 was operated in a low Earth orbit, at an epoch of 14 October 1966, it had a perigee of , an apogee of , an inclination of 65.0°, and an orbital period of 89.4 minutes. After seven days in orbit, Kosmos 129 was deorbited, with its return capsule descending under parachute, landing at 06:14 GMT on 21 October 1966, and recovered by Soviet force.

Kosmos 132 was operated in a low Earth orbit, at an epoch of 19 November 1966, it had a perigee of , an apogee of , an inclination of 65.0°, and an orbital period of 89.3 minutes. After spending eight days in orbit, Kosmos 132 was deorbited with its return capsule descending under parachute, landing at 07:12 GMT on 27 November 1966, and recovered by Soviet force.

Explorer 39, also known as AD-C (Air Density C), was an American scientific satellite belonging to series Air Density. It was launched on August 8, 1968, join with Explorer 40, from Launch Complex 5 of the Vandenberg Air Force Base, through a Scout rocket. Explorer 39 orbited the Earth once every 118.2 minutes, at an inclination of 80.6°. Its perigee was and apogee was .

Supermoons will be the marked points nearest the bottom of the graph. The oscillating nature of the distance to the full or new moon is due to the difference between the synodic and anomalistic months. The period of this oscillation is about 14 synodic months, which is close to 15 anomalistic months. So every 14 lunations there is a Full Moon nearest to perigee.

Intelsat 604 initially operated in a geostationary orbit with a perigee of , an apogee of , and 0.3 degrees of inclination, however over time this became more inclined. The satellite carried 38 IEEE C band and ten IEEE transponders, and had a design life of 13 years and a mass of . Following its arrival in geostationary orbit, Intelsat 604 was deployed at a longitude of 38 degrees west.

Kosmos 173 was operated in an orbit with a perigee of , an apogee of , an inclination of 71.0°, and an orbital period of 92.3 minutes. It remained in orbit until it decayed and reentered the atmosphere on 17 December 1967. It was the ninth of seventy nine DS-P1-Yu satellites to be launched, and the eighth of seventy two to successfully reach orbit.

Lunar Perigee will occur on Monday, August 10, 2026, two days before the total solar eclipse. The total eclipse will pass over northern Spain from the Atlantic coast to the Mediterranean coast as well as the Balearic Islands. The total eclipse will be visible from the cities of Valencia, Zaragoza, Palma and Bilbao but both Madrid and Barcelona will be just outside the path of totality.

Upon successfully reaching orbit, it was assigned the Harvard designation 1962 Alpha Upsilon 1. FTV-1132 was operated in a low Earth orbit, with a perigee of , an apogee of , 82.8 degrees of inclination, and a period of 94.2 minutes. The satellite had a mass of , and was equipped with a frame camera with a focal length of , which had a maximum resolution of .

The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. USA-203 is located in an orbit with a perigee of , an apogee of , a period of 718 minutes, and 55.8 degrees of inclination to the equator. It was intended to operate in slot 2 of plane B of the GPS constellation, replacing USA-128, and to broadcast signal PRN-01.

The launch took place from Launch Complex 17A at the Cape Canaveral Air Force Station, and placed USA-132 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 22 August 1997, USA-132 was in an orbit with a perigee of , an apogee of , a period of 718.08 minutes, and 54.9 degrees of inclination to the equator.

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 11 October 1992, USA-84 was in an orbit with a perigee of , an apogee of , a period of 717.98 minutes, and 54.7 degrees of inclination to the equator. It had PRN 27, and operated in slot 4 of plane A of the GPS constellation. The satellite has a mass of .

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 5 March 1993, USA-88 was in an orbit with a perigee of , an apogee of , a period of 717.9 minutes, and 54.8 degrees of inclination to the equator. It broadcast PRN 22, and operated in slot 1 of plane B of the GPS constellation. The satellite had a mass of .

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 2 May 1993, USA-90 was in an orbit with a perigee of , an apogee of , a period of 717.96 minutes, and 54.9 degrees of inclination to the equator. It broadcast PRN 31, and operated in slot 3 of plane C of the GPS constellation. The satellite had a mass of .

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 27 March 1992, USA-79 was in an orbit with a perigee of , an apogee of , a period of 717.9 minutes, and 54.7 degrees of inclination to the equator. It had PRN 25, and operated in slot 2 of plane A of the GPS constellation. The satellite had a mass of .

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 12 May 1992, USA-80 was in an orbit with a perigee of , an apogee of , a period of 717.94 minutes, and 55.1 degrees of inclination to the equator. It had PRN 28, and operated in slot 2 of plane C of the GPS constellation. The satellite had a mass of .

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 6 August 1992, USA-83 was in an orbit with a perigee of , an apogee of , a period of 717.92 minutes, and 55 degrees of inclination to the equator. It has PRN 26, and operates in slot 2 of plane F of the GPS constellation. The satellite has a mass of .

OPS 5114 was placed into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-27 apogee motor. By 1 February 1979, OPS 5114 was in an orbit with a perigee of , an apogee of , a period of 717.96 minutes, and 63.2 degrees of inclination to the equator. The satellite had a design life of 5 years and a mass of .

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 25 January 1993, USA-87 was in an orbit with a perigee of , an apogee of , a period of 717.94 minutes, and 54.7 degrees of inclination to the equator. It had PRN 29, and operated in slot 5 of plane F of the GPS constellation. The satellite had a mass of .

Abbott and Costello in Hollywood. New York: Perigee Books. After the Mutual Wheel collapsed during the Great Depression, Costello went to work for stock burlesque impresarios, including the Minskys, where he crossed paths with a talented producer and straight man named Bud Abbott. They first worked together in 1935 at the Eltinge Theatre on 42nd Street in New York City after Costello's straight man fell ill.

PerúSAT-1, with a mass of approximately , was in the lower position and was the last satellite to be separated, approximately 1 hour, 42 minutes and 59 seconds after lift-off. It was deployed into a sun-synchronous orbit with perigee and apogee altitudes of respectively and , and an inclination of 98.2° as target. It later reached autonomously its quasi-circular operational orbit at in altitude.

Kosmos 967 was placed into a low Earth orbit with a perigee of , an apogee of , 65.8 degrees of inclination, and an orbital period of 104.7 minutes. It was successfully intercepted by Kosmos 970 in a non-destructive test on 21 December 1977. It was then re-used by Kosmos 1009 on 19 May 1978. Both tests were successful, and both left Kosmos 967 intact.

ADOPTION: The Essential Guide to Adopting Quickly and Safely, by Randall Hicks, Perigee Press 2007 To assist in the adoption of waiting children, there is a U.S. government-affiliated website, AdoptUSKids.org, assisting in sharing information about these children with potential adoptive parents. The North American Council on Adoptable Children provides information on financial assistance to adoptive parents (called adoption subsidies) when adopting a child with special needs.

Kosmos 324 was the thirtieth of seventy nine DS-P1-Yu satellites to be launched, and the twenty-eighth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 91 minutes. It remained in orbit until it decayed and reentered the atmosphere on 23 May 1970.

Kosmos 334 was the thirty-first of seventy nine DS-P1-Yu satellites to be launched, and the twenty-ninth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.4 minutes. It remained in orbit until it decayed and reentered the atmosphere on 9 August 1970.

Kosmos 319 was operated in an orbit with a perigee of , an apogee of , 81.9 degrees of inclination, and an orbital period of 100.5 minutes. It remained in orbit until it decayed and reentered the atmosphere on 1 July 1970. It was the twenty-ninth of seventy nine DS-P1-Yu satellites to be launched, and the twenty-seventh of seventy two to successfully reach orbit.

In general, the oblateness of the Earth perturbs the argument of perigee (\omega), so that even if the apogee started near the north pole, it would gradually move unless constantly corrected with station- keeping thruster burns. Keeping the dwell point over Russia, and useful for communications necessitated without excessive fuel use meant that the satellites needed an inclination of 63.4°, for which these perturbations are zero.

Kosmos 380 was the thirty-seventh of seventy nine DS-P1-Yu satellites to be launched, and the thirty-fourth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 81.9 degrees of inclination, and an orbital period of 100.6 minutes. It remained in orbit until it decayed and reentered the atmosphere on 17 June 1971.

Kosmos 388 was the thirty-eighth of seventy nine DS-P1-Yu satellites to be launched, and the thirty-fifth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 92 minutes. It remained in orbit until it decayed and reentered the atmosphere on 10 May 1971.

Kosmos 357 was the thirty-fifth of seventy nine DS-P1-Yu satellites to be launched, and the thirty-second of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.5 minutes. It remained in orbit until it decayed and reentered the atmosphere on 24 November 1970.

Kosmos 369 was the thirty-sixth of seventy nine DS-P1-Yu satellites to be launched, and the thirty-third of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.6 minutes. It remained in orbit until it decayed and reentered the atmosphere on 22 January 1971.

Kosmos 347 was the thirty-third of seventy nine DS-P1-Yu satellites to be launched, and the thirtieth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 48.4 degrees of inclination, and an orbital period of 107.1 minutes. It remained in orbit until it decayed and reentered the atmosphere on 7 November 1971.

Kosmos 351 was the thirty-fourth of seventy nine DS-P1-Yu satellites to be launched, and the thirty-first of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.43 minutes. It remained in orbit until it decayed and reentered the atmosphere on 13 October 1970.

The perigee is similar to the cruising altitude of most modern airliners, and within Earth's atmosphere. Petit published another paper on his 1846 observations in 1861, basing the second moon's existence on perturbations in movements of the actual Moon. This second moon hypothesis was not confirmed either. Petit's proposed moon became a plot point in Jules Verne's 1870 science fiction novel Around the Moon.

INSAT-4A was launched by an Ariane 5, produced by Arianespace, on 22 Dec 2005 at 4.22 am IST from Kourou, French Guiana. It was placed into a Geosynchronous Transfer Orbit (GTO), 30 minutes after lift-off in 3-axis stabilized mode, with a perigee of 859 km and an apogee of 36,055 km. Its co-passenger on board was Meteosat-9 of EUMETSAT.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1968-117A. The North American Aerospace Defense Command assigned it the catalogue number 03624. Kosmos 261 was the first of two DS-U2-GK satellites to be launched. It was operated in an orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 92.68 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1971-105A. The North American Aerospace Defense Command assigned it the catalogue number 05643. Kosmos 461 was the only DS-U2-MT satellite to be launched. It was operated in an orbit with a perigee of , an apogee of , 69.2 degrees of inclination, and an orbital period of 94.55 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1971-052A. The North American Aerospace Defense Command assigned it the catalogue number 05281. Kosmos 426 was the only DS-U2-K satellite to be launched. It was operated in an orbit with a perigee of , an apogee of , 74 degrees of inclination, and an orbital period of 109.2 minutes.

Kosmos 839 was placed into a low Earth orbit with a perigee of , an apogee of , 65.9 degrees of inclination, and an orbital period of 115.6 minutes. It was successfully intercepted by Kosmos 843 on 21 July. As of 2009, debris is still in orbit. Kosmos 839 was the third of ten Lira satellites to be launched, of which all but the first were successful.

It was launched aboard the seventh flight of the Kosmos-2I 63S1 rocket. The launch was conducted from Mayak-2 at Kapustin Yar, and occurred at 16:00:00 GMT on 30 June 1962. Kosmos 6 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 49.0°, and an orbital period of 90.6 minutes. It decayed on 8 August 1962.

Therefore, the Moon takes a little longer to return to perigee than to return to the same star. A draconic month is shorter than a sidereal month because the nodes move in the opposite direction as the Moon is orbiting the Earth, one revolution in 18.6 years. Therefore, the Moon returns to the same node slightly earlier than it returns to the same star.

The spacecraft was operated at a longitude of 176° east until 1970, before being moved to 166° west. In total the satellite remained in service for around three and a half years. As of February 8, 2014 the derelict Intelsat II F-4 was in an orbit with a perigee of , an apogee of , inclination of 6.00 degrees and an orbital period of 23.95 hours.

In the event, the mission was successful, as was each of the next 13 Falcon 9 v1.1 missions before a launch vehicle failure and loss of mission occurred on Falcon 9 Flight 19 in June 2015. The Falcon 9 upper stage used to launch CASSIOPE was left derelict in a decaying elliptical low Earth orbit that, , had a perigee of and an apogee of .

Cerise (French for "cherry") was a French military reconnaissance satellite. Its main purpose was to intercept HF radio signals for French intelligence services. With a mass of 50 kg, it was launched by an Ariane rocket from Kourou in French Guiana at 17:23 UT, 7 July 1995. Cerise's initial orbital parameters were period 98.1 min, apogee 675 km, perigee 666 km, and inclination 98.0 deg.

New York: Perigee Books. Produced during a slump in Charles Laughton's career, the accomplished actor signed on to do the film for a mere $25,000. Shortly after filming was completed, on April 6, Abbott and Costello hosted an episode of the Colgate Comedy Hour and brought Laughton along as a guest. Later that year, the three of them filmed a two-minute commercial for Christmas Seals.

Kosmos 25 was placed into a low Earth orbit with a perigee of , an apogee of , 49.0° of inclination, and an orbital period of 92.3 minutes. It decayed from orbit on 21 November 1964. Kosmos 25 was a prototype DS-P1 satellite, the last of four to be launched. Of these, it was the third to successfully reach orbit after Kosmos 6 and Kosmos 19.

International reference guide to space launch systems, Fourth Edition, p. 334, Initially, a leak of helium gas from one of the components in the fourth stage was suspected, similar to recent Long March 3 launch failure, but later ruled out. Resulting orbit was partially corrected using satellite's on-board thrusters, thereby raising the perigee to 737 km, while the apogee remained at 821 km.

The payload weighed , and was built into the fairing pods of the Atlas missile. Combined weight of the total on-orbit package was . SCORE was launched into an orbit with a perigee of , an apogee of from LC-11 at Cape Canaveral Missile Test Annex, Florida, inclined at 32.3°, with a period of 101.4 minutes. Its batteries lasted 12 days and it reentered the atmosphere on 21 January 1959.

For example, on 1 February 1958 the Explorer 1 satellite was launched into an orbit with a perigee of . It remained in orbit for more than 12 years before its atmospheric reentry over the Pacific Ocean on 31 March 1970. However, the exact behaviour of objects in orbit depends on altitude, their ballistic coefficient, and details of space weather which can affect the height of the upper atmosphere.

The second de-orbit engine burn lasted for approximately 9 minutes and was completed at 16:34. Following the second de-orbit maneuver, the HTV-1 was inserted into an elliptic orbit with an altitude of a perigee of and an apogee of . HTV-1 began the third and final de-orbit maneuver at 20:53 on 1 November 2009 as planned, while the spacecraft was passing over Central Asia.

In June 2011 IBEX shifted to a new orbit that raised its perigee to more than . The new orbit has a period of one third of a lunar month, which, with the correct phasing, avoids taking the spacecraft too close to the Moon, whose gravity can negatively affect IBEX's orbit. Now the spacecraft uses less fuel to maintain a stable orbit, increasing its useful lifespan to more than 40 years.

Ring predicts earthquakes based on the position of the moon. On his website he says that when the moon (in particular the new moon) is at perigee (closest to the earth) it may affect the Earth's mantle and alter the magnetic field. It may also draw the Van Allen Belt closer, attracting radioactively charged particles towards Earth. Ring believes this combination may be responsible for earthquakes and volcanoes.

In addition to its navigation payloads, the satellite also carries a Cospas-Sarsat search and rescue payload. The satellite is located in a medium Earth orbit with an apogee of , a perigee of , and 64.8° of inclination. It is equipped with two solar panels to generate power, and is expected to remain in service for ten years. It is expected to enter service by the end of 2011.

For the repetition of a solar eclipse, the geometric alignment of the Earth, Moon and Sun, as well as some parameters of the lunar orbit should be repeated. The following parameters and criteria must be repeated for the repetition of a solar eclipse: # The Moon must be in new phase. # The longitude of perigee of the Moon must be the same. # The longitude of the ascending node must be the same.

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 11 July 1989, USA-38 was in an orbit with a perigee of , an apogee of , a period of 717.92 minutes, and 54.5 degrees of inclination to the equator. It operated in slot 3 of plane B of the GPS constellation. The satellite had a mass of , and generated 710 watts of power.

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 19 September 1989, USA-42 was in an orbit with a perigee of , an apogee of , a period of 717.86 minutes, and 54.9 degrees of inclination to the equator. The satellite had a mass of , and generated 710 watts of power. It had a design life of 7.5 years, and ceased operations on 13 October 2000.

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 21 November 1989, USA-47 was in an orbit with a perigee of , an apogee of , a period of 717.9 minutes, and 54.7 degrees of inclination to the equator. It operated in slot 5 of plane A of the GPS constellation. The satellite had a mass of , and generated 710 watts of power.

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 11 January 1990, USA-49 was in an orbit with a perigee of , an apogee of , a period of 718 minutes, and 54.9 degrees of inclination to the equator. It operated in slot 3 of plane D of the GPS constellation. The satellite had a mass of , and generated 710 watts of power.

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 3 September 1990, USA-63 was in an orbit with a perigee of , an apogee of , a period of 718 minutes, and 54.7 degrees of inclination to the equator. It operated in slot 2 of plane E of the GPS constellation. The satellite had a mass of , and generated 710 watts of power.

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 17 October 1996, USA-128 was in an orbit with a perigee of , an apogee of , a period of 717.94 minutes, and 54.7 degrees of inclination to the equator. It broadcasts the PRN 30 signal, and operates in slot 2 of plane B of the GPS constellation. The satellite has a mass of .

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 13 December 1997, USA-135 was in an orbit with a perigee of , an apogee of , a period of 717.9 minutes, and 54.9 degrees of inclination to the equator. It broadcasts the PRN 08 signal, and operates in slot 3 of plane A of the GPS constellation. The satellite has a mass of .

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 27 July 1993, USA-92 was in an orbit with a perigee of , an apogee of , a period of 717.96 minutes, and 54.7 degrees of inclination to the equator. It broadcasts the PRN 09 signal, and operates in slot 1 of plane A of the GPS constellation. The satellite has a mass of .

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 25 November 1993, USA-96 was in an orbit with a perigee of , an apogee of , a period of 717.96 minutes, and 55 degrees of inclination to the equator. It broadcast the PRN 04 signal, and operated in slot 4 of plane D of the GPS constellation. The satellite has a mass of .

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 15 April 1994, USA-100 was in an orbit with a perigee of , an apogee of , a period of 716.69 minutes, and 54.9 degrees of inclination to the equator. It broadcasts the PRN 06 signal, and operates in slot 1 of plane C of the GPS constellation. The satellite has a mass of .

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 27 April 1996, USA-117 was in an orbit with a perigee of , an apogee of , a period of 717.96 minutes, and 54.7 degrees of inclination to the equator. It broadcasts the PRN 03 signal, and operates in slot 2 of plane C of the GPS constellation. The satellite has a mass of .

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 15 August 1996, USA-126 was in an orbit with a perigee of , an apogee of , a period of 717.9 minutes, and 55 degrees of inclination to the equator. It broadcasts the PRN 10 signal, and operates in slot 3 of plane E of the GPS constellation. The satellite has a mass of .

It weighed about at launch. Launch aboard an Ariane 5GS rocket took place on 2007-12-21. On 2007-12-29 Thales Alenia Space announced that a helium leak aboard the spacecraft would delay its activation. On 2008-01-08 the company announced the perigee of the satellite's orbit would be raised, and also acknowledged that if the satellite eventually reached geostationary orbit its useful lifetime would be significantly reduced.

The launch occurred from Site 43/4 at the Plesetsk Cosmodrome at 08:34:44 GMT on 24 December 2006. It was constructed by ISS Reshetnev and is believed to be based on the Uragan-M satellite bus, which has also been used for GLONASS navigation satellites. It operates in a Molniya orbit with a perigee of , an apogee of , and 65° inclination. The satellite entered service on 1 February 2007.

NEXTSat is a spacecraft, which was built by Ball Aerospace around the RS-300 satellite bus. It was operated in low Earth orbit; on 9 March 2007, it had a perigee of , an apogee of , 46.0 degrees of inclination, and an orbital period of 94.49 minutes. After completing operations, the ASTRO and NEXTSat spacecraft were separated, and ASTRO performed a separation burn. On 21 July 2007, NEXTSat was deactivated.

In the month following depletion of coolant the 'Technology Test Phase' (TTP) was initiated to test several elements of the satellite in off-nominal conditions. After completion of TTP, the perigee of ISO's orbit was lowered sufficiently enough to ensure ISO will burn up in Earth's atmosphere in 20 to 30 years after shutdown. ISO was then permanently switched off on May 16, 1998, at 12:00 UTC.

The Film Encyclopedia: The Most Comprehensive Encyclopedia of World Cinema in a Single Volume. Perigee Books. . Pp. 972–973. He received his first film roles in 1929, appearing in Song of Love, followed by Their Own Desire, both of which were uncredited. In 1930 he had two more uncredited roles, then landed the lead role in the boxing serial The Leather Pushers, an 11-film series that ran into 1931.

On 23 October 2019 Southern Launch made a joint announcement with Perigee Aerospace of South Korea about the launch of the Blue Whale 1 rocket from the Whalers Way facility. On 20 February 2020 Southern Launch signed a contract with DEWC Systems for the provision of launch services using the T-Minus Engineering DART rocket. The launch was carried out from the Koonibba Test Range on 19 September 2020.

Spacecraft with a perigee below about are subject to drag from the Earth's atmosphere, which decreases the orbital altitude. The rate of orbital decay depends on the satellite's cross- sectional area and mass, as well as variations in the air density of the upper atmosphere. Below about , decay becomes more rapid with lifetimes measured in days. Once a satellite descends to , it has only hours before it vaporizes in the atmosphere.

First stage engines cut off at T+02:56, nose cone separated at T+03:47, second stage engines cut off at T+08:56, all as planned. The Dragon vehicle separated at T+09:30 and achieved a near circular orbit, with a perigee of , an apogee of and an inclination of 34.53°. These were close to targeted marks of a circular orbit at an inclination of 34.5°.

Kosmos 959 was placed into a low Earth orbit with a perigee of , an apogee of , 65.8 degrees of inclination, and an orbital period of 94.6 minutes. It was successfully intercepted by Kosmos 961, as part of a non-destructive test. Following this, it decayed from orbit on 30 November 1977. Kosmos 959 was the sixth of ten Lira satellites to be launched, of which all but the first were successful.

It was identified as NRO Launch 41, and was the twenty-third flight of an Atlas V; the vehicle had the tail number AV-025, and was named Gladys. The satellite's orbit and mission are officially classified; however, it has been located by amateur observers in a retrograde low Earth orbit. As of it was in an orbit with a perigee of , an apogee of and degrees of inclination.

Eight of the eleven experiments were successful. The hatch installed in the Gemini's heat shield to provide access to the MOL during crewed operations was tested during the capsule's reentry. The Gemini capsule was recovered near Ascension Island in the South Atlantic by the after a flight of 33 minutes. The laboratory mockup entered an orbit with an apogee of , a perigee of , and 32.8 degrees of inclination.

Draco thrusters generate 400 newtons (90 pounds-force) of thrust using a storable propellant mixture of monomethyl hydrazine fuel and nitrogen tetroxide oxidizer. The Draco thrust is comparable to the Marquardt R-4D engine developed for the Apollo Service and Lunar Modules in the 1960s and used for apogee/perigee maneuvers, orbit adjustment, and attitude control. Sixteen Draco thrusters are used on the Dragon spacecraft for attitude control and maneuvering.

Ariel 3 had an orbital period of approximately 95 minutes, with an apogee of 608 km and a perigee of 497 km. It initially spun at 31 rpm for stability, though by the time the Ariel 3 deorbited, it had slowed to a rate of about 1 rpm. On 24 October 1967 the tape recorder aboard Ariel 3 began to malfunction. This restricted observation to real-time operation only.

In May 2011, the news agency RIA Novosti reported that the BMSV instrument would indeed be on board. It was also reported that the BMSV would carry a micrometeoroid counter made in Germany. The RadioAstron was expected to extend into a highly elliptical orbit in the Fregat state of the Zenit rocket's launch. Spektr-R's closest point (perigee) would be above the Earth's surface, with its apogee away.

ESSA-9 was launched on a three-stage Delta rocket from Cape Canaveral, Florida. The launch occurred at 07:47 UTC (02:47 EDT) on February 26, 1969. The spacecraft was placed in a sun-synchronous orbit of 101.4° inclination. Immediately after launch ESSA-9 had a perigee of and an apogee of , giving it an orbital period of 115.2 minutes, or a mean motion of 12.5 orbits per day.

These correspond to seasonal changes, perigee/apogee tidal variation, and neap/spring tidal variation, respectively. Together, the different cycles reconstruct a deltaic environment near the equator which was heavily influenced by tides and a monsoonal climate. Modern equivalents would be the deltas of the Amazon, Ganges/Brahmaputra, and Fly rivers. During glacial periods, the monsoonal climate would have mellowed out into a less seasonal tropical climate in equatorial regions.

Putnam purchased the company in 1991, and the offices were moved to New York. Tarcher remained head of the company until early 1996, and Joel Fotinos was named Publisher later that year. Tarcher merged with sister imprint Perigee to form TarcherPerigee in 2015. TarcherPerigee publications cover a broad spectrum of topics in the areas of wellness, self-improvement, spirituality, esoterica, occultism, creativity, social consciousness, prosperity and abundance, and more.

The Moon's orbit approximates an ellipse rather than a circle. However, the orientation (as well as the shape) of this orbit is not fixed. In particular, the position of the extreme points (the line of the apsides: perigee and apogee), rotates once (apsidal precession) in about 3,233 days (8.85 years). It takes the Moon longer to return to the same apsis because it has moved ahead during one revolution.

The ATDA is launched from Cape Kennedy's Pad 14 atop an Atlas launch vehicle at 10 a.m., June 1, 1966. Tom Stafford inside the Gemini spacecraft Stafford made the first thruster burn 49 minutes after launch, to add to their speed, raising their perigee from . An hour and 35 minutes later, Stafford corrected phase, height, and out-of-plane errors by pointing the spacecraft 40° down, and 3° to the left.

The launch was conducted by Kosmotras with liftoff occurring at 07:12:20 on 17 August 2011. The rocket carried six other satellites, with an additional payload bolted to the upper stage. The satellite was placed into a sun-synchronous low Earth orbit. As of 22 November 2013 it was in an orbit with a perigee of , an apogee of , 98.20 degrees inclination and a period of 98.04 minutes.

On 15 April 1968 at 09:34:18 GMT, the Soyuz 11A511 s/n U15000-06 booster and Kosmos 213 were set up at Site 1/5 of Baikonur Cosmodrome and the planned mission could be carried out. Kosmos 213 was operated in a low Earth orbit, it had a perigee of , an apogee of , an inclination of 51.4°, and an orbital period of 89.16 minutes, and had a mass of .

Kosmos 400 was placed into a low Earth orbit with a perigee of , an apogee of , 65.8 degrees of inclination, and an orbital period of 105 minutes. It was successfully intercepted and destroyed by Kosmos 404 on 4 April. As of 2009, debris is still in orbit. Kosmos 400 was the third of the five original DS-P1-M satellites to be launched, of which all but the first were successful.

The comet reached its perihelion (the point that is closest to the Sun) on June 5, 2014, and then its perigee (the point that is closest to Earth) on July 10, 2014, at a distance of about 47 million kilometres. The comet peaked around apparent magnitude 9 and was visible in small telescopes. From late July 2014 until March 2015, as seen from Earth, the comet will appear near Arcturus.

Lotenero has created graphics for The New York Pro Show in New York City, The Quiksilver ProFrance Surf Competition, and the Museum of Contemporary Art San Diego. He is the illustrator for Eva Nagorski's The Down and Dirty Dish on Revenge,Nagorski, Eva (2009), The Down and Dirty Dish on Revenge, St. Martins Macmillan. and Eva Christina's The Book of Kink.Christina, Eva (2011), The Book of Kink, Perigee Penguin.

Moon's compositions are compared to post-minimalist, but defy a strict definition of genre. She released Perigee & Apogee in 2001 on the Albany label and Earthshine on her own label, Bibimbop Records in 2004. In 2007, Naxos Records added a CD of her works for solo piano, performed by Moon herself, to their catalog of important 21st-century composers. Her work has been acclaimed by Kyle Gann, Gramophone, Allmusic, and others.

The full moon cycle is the time for the Sun (as seen from the Earth) to complete one revolution with respect to the perigee of the Moon's orbit. This period is associated with the apparent size of the full moon, and also with the varying duration of the synodic month. The duration of one full moon cycle is: : days (411 days 18 hours 49 minutes 35 seconds) (at the epoch J2000.0).

Abbie Hoffman, Soon to be a Major Motion Picture, page 278. Perigee Books, 1980. Poster advertising Yippie-sponsored Pittsburgh Smoke-In, Schenley Park, July 2, 1977 In 1973, Yippies marched on the Manhattan home of Watergate conspirator John Mitchell: > ... five hundred die-hard Yippies staged one last march on the Mitchell > home, no longer the Watergate but a grand apartment building on Manhattan's > Fifth Avenue. "Free Martha Mitchell!" they chanted.

The state-of-the-art GSAT 7 satellite carrying payloads operating in UHF, S, C and Ku bands, had a lift-off mass of and is based on ISRO's satellite bus with some new technological elements, including the antennae. After a flight of almost 34 minutes, the satellite was injected into a geosynchronous transfer orbit (GTO) of perigee, apogee and an inclination of 3.5 degree with respect to the equator.

2, 2010), Spaceflight Now, "Investigators probing what went wrong with AEHF 1" (accessed Dec. 14, 2011) and it was declared inoperable. To solve the problem, the perigee altitude was raised to 4700 km (2900 miles) using twelve firings of the smaller Reaction Engine Assembly thrusters, originally intended for attitude control during LAE maneuvers.Ray, Justin (October 9, 2011), Spaceflight Now, "Air Force satellite's epic ascent should finish soon" (accessed Dec.

It was assigned the Harvard designation 1961 Alpha Lambda 1. Following launch, FTV-2203 was in a low Earth orbit with an apogee of , a perigee of , and 89.6 degrees of inclination. Within a few days of launch, it was commanded to deorbit in order to return its film capsule. This was conducted, however due to the additional altitude provided by the anomaly during launch, it was unable to fully deorbit.

A geosynchronous orbit can have any inclination. Satellites commonly have an inclination of zero, ensuring that the orbit remains over the equator at all times, making it stationary with respect to latitude from the point of view of a ground observer (and in the ECEF reference frame). Another popular inclinations is 63.4° for a Tundra orbit, which ensures that the orbit's argument of perigee doesn't change over time.

The launch took place at 00:53 UTC (08:53 CST) on 8 December 2006, with the carrier rocket placing the satellite into a geosynchronous transfer orbit. An FG-36 apogee motor was then used to raise the satellite into geosynchronous orbit. By 7 February 2007, it was in an orbit with a perigee of , and apogee of , and 2.4 degrees inclination. It is positioned at a longitude of 86.5 degrees east.

Kosmos 214 was operated in a low Earth orbit, at an epoch of 18 April 1968, it had a perigee of , an apogee of , an inclination of 81.4°, and an orbital period of 90.3 minutes. After eight days in orbit, Kosmos 214 was deorbited, with its return capsule descending under parachute and landing at 09:36 GMT on 26 April 1968, and recovered by the Soviet forces in the steppe in Kazakhstan.

Explorer 50 was a drum-shaped spacecraft, across and height, with propulsion Star-17A, instrumented for interplanetary and magnetotail studies of cosmic rays, energetic solar particles, plasma, and electric and magnetic fields. Its initial orbit was more elliptical than intended, with apogee and perigee distances of about 45 earth radii and 25 earth radii. Its eccentricity decreased after launch. Its orbital inclination varied between 0° and about 55° with a periodicity of several years.

Biosatellite 1, also known as Biosat 1 and as Biosatellite A, was a first artificial satellite unmanned U.S. belonging to Biosatellite program for biological research. It was released on December 14, 1966 by a rocket Delta G from Launch Complex 17A of the Cape Canaveral Air Force Station.Biosatellite 1 was the first series Biosatellite satellites. It was released in an initial orbit of perigee apogee and 33.5 degrees of orbital inclination, with period 90.5 minutes.

The launch of EchoStar XIV was conducted by International Launch Services, using a Proton-M carrier rocket with a Briz-M upper stage. The launch occurred from Site 200/39 at the Baikonur Cosmodrome in Kazakhstan, at 18:26:57 UTC on 20 March 2010. The launch successfully placed EchoStar XIV into a geosynchronous transfer orbit. Following separation from the rocket, it manoeuvered into a geostationary orbit with a perigee of and an apogee of .

Perigee Books. . P.20. Her father cut off her allowance in hopes that she would return home, but her contract with Universal Studios enabled her to continue in Hollywood. During World War II, Allbritton performed overseas with a USO troupe, a group that "[g]ave show after show, many of them to the accompaniment of the thunder of enemy guns." She had a leading role in the Broadway production of The Seven Year Itch.

The launch of FTV-1126 occurred at 19:36 UTC on 15 May 1962. A Thor DM-21 Agena-B rocket was used, flying from Launch Complex 75-3-5 at the Vandenberg Air Force Base. Upon successfully reaching orbit, it was assigned the Harvard designation 1962 Sigma 1. FTV-1126 was operated in a low Earth orbit, with a perigee of , an apogee of , 82.3 degrees of inclination, and a period of 93.75 minutes.

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 25 February 1990, USA-50 was in an orbit with a perigee of , an apogee of , a period of 717.92 minutes, and 54.6 degrees of inclination to the equator. The satellite had a mass of , and generated 710 watts of power. It had a design life of 7.5 years, and was retired from service on 18 August 2000.

Upon successfully reaching orbit, it was assigned the Harvard designation 1960 Tau 1. Discoverer 19 was operated in a low Earth orbit, with a perigee of , an apogee of , 83.4 degrees of inclination, and a period of 92.4 minutes. The satellite had a mass of , and was used to demonstrate technology for the Midas programme, including infrared sensors. It remained in orbit until 23 January 1961, when it decayed and reentered the atmosphere.

A restoration of the program won a technical Emmy in 1988 for Ed Reitan, Don Kent, and Dan Einstein. They restored the original videotape, transferring its contents to a modern format and filling in gaps where the tape had deteriorated with kinescope footage."Emmys" by Thomas O'Neil; Perigee Trade; 3 edition 2000; pp. 61–62 Astaire played Julian Osborne, a non-dancing character, in the nuclear war drama On the Beach (1959).

As of 24 July 2011, USA-232 was in an orbit with a perigee of , an apogee of , a period of 729.16 minutes, and 55.0 degrees of inclination to the equator. It is used to broadcast the PRN 01 signal, and operates in slot 2 of plane D of the GPS constellation. The satellite has a design life of 15 years and a mass of . As of 2019 it remains in service.

A partial solar eclipse occurred on June 21, 1982. A solar eclipse occurs when the Moon passes between Earth and the Sun, thereby totally or partly obscuring the image of the Sun for a viewer on Earth. A partial solar eclipse occurs in the polar regions of the Earth when the center of the Moon's shadow misses the Earth. Occurring only 7 minutes before perigee, the Moon's apparent diameter was completely larger.

Perigee Books, page 558. The Moodys' sons, Carlton Moody, Dave Moody and Trent Moody, known as The Moody Brothers were nominated for a Grammy Award for their instrumental performance of the classic fiddle tune "Cotton Eyed Joe". This record established Lamon as an international label. The trio of brothers would be nominated for a second Grammy on the Lamon family label in 1990 and win three International Country Music Awards in Europe.

Tubsat-N was a German miniaturized satellite for communication designed by the Technical University of Berlin. The satellite was launched on July 7, 1998 by the Russian submarine K-407 Novomoskovsk in Barents Sea using a Shtil' rocket. Tubsat-N had a mass of 8.0 kg (17.60 lb) and measured 32 × 32 × 10.4 cm. The orbit of this satellite had a perigee of 400 km (240 mi) and an apogee of 776 km (482 mi).

Lemond G, Gordis K. "Greg LeMond's Complete Book of Bicycling" New York, Perigee Books,1990 The Gavia was constructed of Columbus TSX tubing. This model was available in red, blue with pearl white panels and pearl white with fluorescent splatter. Jan Ullrich's 1997 Tour de France winning Paris FP The Pinarello Paris in the mid-1990s was a 7005 series aluminium bike with an aluminium fork later replaced by the aria carbon fork.

Kosmos 1171 was placed into a low Earth orbit with a perigee of , an apogee of , 65.8 degrees of inclination, and an orbital period of 104.8 minutes. It was to have been intercepted by Kosmos 1174 on 18 April, however the interceptor malfunctioned and missed the target. Two further attempts over the next two days also failed, before the interceptor was commanded to self-destruct. As of 2009, Kosmos 1171 is still in orbit.

The German Fetish Ball or German Fetish Fair & BDSM Convention is an annual fetish exhibition held in Germany, and known as well under the acronym GFB. The fair has been running since 2003 and has been held in Berlin, then in Hamburg, and now back in Berlin.Eva Christina, The Book of Kink: Sex Beyond the Missionary, New York: Penguin/Perigee, 2011, , n.p.: "The annual German Fetish Ball weekend takes place in Hamburg".

During this time, Progress 39 was used to boost the orbit of the space station. This was necessary due to the greater than normal atmospheric drag. The extra drag was caused by atmospheric expansion, which in turn was caused by the solar maximum occurring at the time, during solar cycle 22. The boost changed the Perigee and Apogee of the station from 325 km and 353 km AMSL to 340 km and 376 km, respectively.

Intelsat 603 operated in a geostationary orbit with a perigee of , an apogee of , and 0.3 degrees of inclination. The satellite carried 38 IEEE C band and ten IEEE transponders, and had a design life of 13 years and a mass of . Upon arrival in geostationary orbit, Intelsat 603 was placed at a longitude of 34.5 degrees west. It remained there until October 1997, when it was moved to 24.5 degrees west, arriving in November.

As of 6 August, AMC-14 orbit is vastly different. Figures for perigee (periapsis), apogee (apoapsis) and Inclination are given in the info box at the beginning of this article, Inclination has dropped to 17.7 and Eccentricity has decreased to 0.199. As of January 29, 2009, after more than 6 months of low-thrust maneuvering, AMC-14 had finally reached an inclined (13.1°) geosynchronous orbit at 34.8°East under US DoD ownership.

New York: Perigee Books. This was actually after the team had already completed Hold That Ghost. The latter was held back for revisions and the naval comedy was released as the team's second starring vehicle. There was, however, one problem before it could be released: when the film was screened for the Navy, officers were offended by the sequence where Pomeroy (Costello) impersonates a captain and puts the battleship through a series of madcap maneuvers.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1967-061A. The North American Air Defense Command assigned it the catalogue number 02848. Kosmos 166 was the first of two DS-U3-S satellites to be launched, the other being Kosmos 230. It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.4°, and an orbital period of 92.6 minutes.

Kosmos 880 was placed into a low Earth orbit with a perigee of , an apogee of , 65.8 degrees of inclination, and an orbital period of 96.3 minutes. It was successfully intercepted and destroyed by Kosmos 886 on 27 December. The last catalogued piece of debris decayed from orbit on 9 December 2001. Kosmos 880 was the fourth of ten Lira satellites to be launched, of which all but the first were successful.

It was launched aboard Kosmos-2I 63S1 s/n 5LK. It was the fourth flight of the Kosmos-2I, and the second to successfully reach orbit. The launch was conducted from Mayak-2 at Kapustin Yar, and occurred at 17:16:00 GMT on 6 April 1962. Kosmos 2 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 49.0°, and an orbital period of 102.5 minutes.

It was launched aboard Kosmos-2I 63S1 s/n 4LK. It was the fifth flight of the Kosmos-2I, and the third to successfully reach orbit. The launch was conducted from Mayak-2 at Kapustin Yar, and occurred at 04:04:00 GMT on 24 April 1962. Kosmos 3 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 49.0°, and an orbital period of 93.8 minutes.

It was launched aboard Kosmos-2I 63S1 s/n 3LK. It was the sixth flight of the Kosmos-2I, and the fourth to successfully reach orbit. The launch was conducted from Mayak-2 at Kapustin Yar, and occurred at 03:07:00 GMT on 28 May 1962. Kosmos 5 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 49.1°, and an orbital period of 102.8 minutes.

In addition to its navigation payloads, the satellite also carries a Cospas-Sarsat search and rescue payload. The satellite is located in a medium Earth orbit with a perigee of , an apogee of , and 64.8° of inclination. It is equipped with two solar panels to generate power, and is expected to remain in service for ten years. Kosmos 2501 was launched from Site 43/4 at the Plesetsk Cosmodrome in northwest Russia.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1976-084A. The North American Aerospace Defense Command assigned it the catalogue number 09387. Kosmos 850 was the last of seventy nine DS-P1-Yu satellites to be launched, of which seventy two successfully achieved orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 92 minutes.

The last burn, during the third orbit, lowered the perigee to . This was made so, in case the retrorockets had failed, the spacecraft would still have reentered the atmosphere. The experience of reentry initially matched expectations, with even the color and pattern of the plasma sheath that enveloped the capsule matching those produced for ground simulations. However, it soon became clear that Molly Brown was off course and would land off target.

The flight took Glenn to a maximum altitude (apogee) of about and a minimum altitude of (perigee). The flight made Glenn the first American to orbit the Earth, the third American in space, and the fifth human in space. The mission, which Glenn called the "best day of his life", renewed U.S. confidence. His flight occurred while the U.S. and the Soviet Union were embroiled in the Cold War and competing in the Space Race.

Unfortunately, a failure in the solar power panels resulted in the termination of operations on 29 January 1976, after slightly less than 4 months of useful life. However, all the regions at the perigee altitudes were sampled during this time. The spacecraft re-entered the atmosphere about 1 month after cessation of telemetry. To continue the correlated observations with the Explorer 55 mission, Explorer 51 was reactivated on 28 February 1976, to replace Explorer 54.

On 25 March 2015, USA-260 was in an orbit with a perigee of , an apogee of , a period of 729.14 minutes, and 55.00 degrees of inclination to the equator. It is used to broadcast the PRN 26 signal, and operates in slot 5 of plane B of the GPS constellation. The satellite has a design life of 15 years and a mass of . It is currently in service following commissioning on April 20, 2015.

The launch occurred on 7 February 1969 at 13:59 UTC, and resulted in Kosmos 265's successful deployment into low Earth orbit. Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1969-012A. Kosmos 265 was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.3 minutes. It remained in orbit until it decayed and reentered the atmosphere on 1 May 1969.

SpaceX was contracted to launch AsiaSat 6 / Thaicom 7 using a Falcon 9 v1.1 launch vehicle. The launch took place from Space Launch Complex 40 at the Cape Canaveral Air Force Station on 7 September 2014. The Falcon 9 upper stage used to launch AsiaSat 6 / Thaicom 7 was derelict in a decaying elliptical low- Earth orbit from September to December 2014. Initially, on 9 September 2014, it orbited with a perigee of and an apogee of .

As of 29 October 2014, USA-258 was in an orbit with a perigee of , an apogee of , a period of 729.56 minutes, and 55.00 degrees of inclination to the equator. It is used to broadcast the PRN 03 signal, and operates in slot 1 of plane E of the GPS constellation. The satellite has a design life of 15 years and a mass of . It is currently in service following commissioning on December 12, 2014.

It was a successful mission that created false confidence just before a string of failures that would follow. Kosmos 146 was launched using a Proton-K carrier rocket, which flew from Site 81/23 at Baikonur. The launch occurred at 11:30:33 GMT on 10 March 1967 and was successful. Kosmos 146 was operated in an Earth orbit, it had a perigee of , an apogee of , an inclination of 51.5° and an orbital period of 89.2 minutes.

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 16 March 1989, USA-35 was in an orbit with a perigee of , an apogee of , a period of 713.2 minutes, and 55.1 degrees of inclination to the equator. The satellite had a mass of , and generated 710 watts of power. It had a design life of 7.5 years; however, it operated until 26 March 2000, when its reaction wheels failed.

Upon successfully reaching orbit, it was assigned the Harvard designation 1961 Zeta 1. Discoverer 21 was operated in a low Earth orbit, with a perigee of , an apogee of , 80.7 degrees of inclination, and a period of 97.4 minutes. The satellite had a mass of , and was used to demonstrate an engine restart, and to test infrared sensors for the Midas programme. It remained in orbit until 20 April 1962, when it decayed and reentered the atmosphere.

On 14 August 1991, USA-71 was in an orbit with a perigee of , an apogee of , a period of 717.86 minutes, and 55.1 degrees of inclination to the equator. It has PRN 24, and operated in slot 1 of plane D of the GPS constellation until it was removed from service in September 2009. It was subsequently relocated, was operational again, briefly covering slot 2 in 2011, before being deactivated in November after USA-232 replaced it.

The satellite raised itself into medium Earth orbit using a Star-27 apogee motor. By 11 April 1978, OPS 5111 was in an orbit with a perigee of , an apogee of , a period of 718 minutes, and 63.3 degrees of inclination to the equator. The satellite had a design life of 5 years and a mass of . It broadcast the PRN 04 signal in the GPS demonstration constellation, and was retired from service on 17 July 1985.

The satellite raised itself into medium Earth orbit using a Star-27 apogee motor. By 20 June 1978, OPS 5112 was in an orbit with a perigee of , an apogee of , a period of 715.67 minutes, and 63.1 degrees of inclination to the equator. The satellite had a design life of 5 years and a mass of . It broadcast the PRN 07 signal in the GPS demonstration constellation, and was retired from service in early-mid February 1988.

The satellite raised itself into medium Earth orbit using a Star-27 apogee motor. By 12 March 1980, OPS 5117 had been raised to an orbit with a perigee of , an apogee of , a period of 717.94 minutes, and 63.2 degrees of inclination to the equator. The satellite had a design life of 5 years and a mass of . It broadcast the PRN 05 signal in the GPS demonstration constellation, and was retired from service on 11 May 1984.

The satellite raised itself into medium Earth orbit using a Star-27 apogee motor. By 8 November 1985, USA-10 had been raised to an orbit with a perigee of , an apogee of , a period of 717.94 minutes, and 63.3 degrees of inclination to the equator. The satellite had a design life of 5 years and a mass of . It broadcast the PRN 03 signal in the GPS demonstration constellation, and was retired from service on 14 April 1994.

The satellite raised itself into medium Earth orbit using a Star-27 apogee motor. By 14 August 1983, OPS 9794 had been raised to an orbit with a perigee of , an apogee of , a period of 717.96 minutes, and 62.8 degrees of inclination to the equator. The satellite had a design life of 5 years and a mass of . It broadcast the PRN 11 signal in the GPS demonstration constellation, and was retired from service on 4 May 1993.

The satellite raised itself into medium Earth orbit using a Star-27 apogee motor. By 14 July 1984, USA-1 had been raised to an orbit with a perigee of , an apogee of , a period of 717.94 minutes, and 62.5 degrees of inclination to the equator. The satellite had a design life of 5 years and a mass of . It broadcast the PRN 13 signal in the GPS demonstration constellation, and was retired from service on 20 June 1994.

The satellite raised itself into medium Earth orbit using a Star-27 apogee motor. By 8 October 1984, USA-5 had been raised to an orbit with a perigee of , an apogee of , a period of 717.98 minutes, and 63.2 degrees of inclination to the equator. The satellite had a design life of 5 years and a mass of . It broadcast the PRN 12 signal in the GPS demonstration constellation, and was retired from service on 26 March 1996.

The satellite raised itself into medium Earth orbit using a Star-27 apogee motor. By 27 May 1980, OPS 5118 had been raised to an orbit with a perigee of , an apogee of , a period of 717.94 minutes, and 62.8 degrees of inclination to the equator. The satellite had a design life of 5 years and a mass of . It broadcast the PRN 09 signal in the GPS demonstration constellation, and was retired from service on 6 March 1991.

Uhuru was the first satellite launched specifically for the purpose of X-ray astronomy. It was also known as the X-ray Explorer Satellite, SAS-A (for "Small Astronomy Satellite" A, being first of the three-spacecraft SAS series), SAS 1, or Explorer 42. The observatory was launched on December 12, 1970 into an initial orbit of about 560 km apogee, 520 km perigee, 3 degrees inclination, with a period of 96 minutes. The mission ended in March 1973.

Upon successfully reaching orbit, it was assigned the Harvard designation 1961 Xi 1. Discoverer 25 was operated in a low Earth orbit, with a perigee of , an apogee of , 82.1 degrees of inclination, and a period of 90.4 minutes. The satellite had a mass of , and was equipped with a panoramic camera with a focal length of , which had a maximum resolution of . Images were recorded onto film, and returned in a Satellite Recovery Vehicle two days after launch.

In Frankel's childhood, gambling equated to friendship, food and laughter. "We bet on everything, from sports to how much our mothers would lose at Weight Watchers," Frankel recalls in the book. Her second book, Brazilian Sexy: Secrets to Living a Gorgeous and Confident Life (co-written with Janea Padilha) was published in April 2010 (Perigee/Penguin Group). Her essay "Looped Yarn" appears in the anthology Knitting Yarns: Writers on Knitting (2013), published by W. W. Norton & Company.

As of 15 July 2015, USA-262 was in an orbit with a perigee of , an apogee of , a period of 728.77 minutes, and 55.00 degrees of inclination to the equator. It is used to broadcast the PRN 08 signal, and operates in slot 3 of plane C of the GPS constellation. The satellite has a design life of 15 years and a mass of . It is currently in service following commissioning on August 12, 2015.

Childrey made observations on the tides at Weymouth, near Upwey. These led him, around 1669, to contest the views of John Wallis and Samuel Colepresse of Plymouth, on the occurrence of the highest tides in February and November; he attributed their findings mainly to winds. His own work had led him to think the Moon's perigee was relevant. Wallis was already embroiled in correspondence on tides with another "country virtuoso", Francis Jessop, but Childrey had a better case.

Relay 1 was launched atop a Delta B rocket on December 13, 1962 from LC-17A at Cape Canaveral Air Force Station. Its payload included radiation experiments designed to map the Earth's radiation belts. Apogee was 7500 km; perigee 1300. The spin-stabilized satellite had an initial spin rate of 167.3 rpm and an initial spin axis orientation with a declination of -68.3 deg and a right ascension of -56 deg. Its orbital period was 185.09 minutes.

MIMOSA ( _Mi_ cro _m_ easurements _o_ f _S_ atellite _A_ cceleration), COSPAR 2003-031B, was a Czech scientific microsatellite. The satellite was nearly spherical with 28 sides and carried a microaccelerometer to monitor the atmospheric density profile by sensing the atmospheric drag on the approximated sphere. MIMOSA was launched on June 30, 2003 alongside other miniature satellites including MOST and several CubeSat-based satellites. It had a fairly eccentric orbit, with an initial perigee of and apogee of .

Parus satellites are produced by JSC Information Satellite Systems (formerly NPO PM), based on the KAUR-1 satellite bus. They have a mass of around , and a design life of 18–24 months. The satellites operate in low Earth orbits, typically with a perigee of about , an apogee of and 82.9° inclination. They are operated by the Russian Aerospace Defence Forces, and are used primarily for navigation, Store and forward communication, and to relay data from US-P satellites.

As of 22 April 2014, USA-248 was in an orbit with a perigee of , an apogee of , a period of 717.99 minutes, and 54.96 degrees of inclination to the equator. It is used to broadcast the PRN 30 signal, and operates in slot 6 of plane A of the GPS constellation. The satellite has a design life of 15 years and a mass of . It is currently in service following commissioning on May 30, 2014.

Kosmos 803 was placed into a low Earth orbit with a perigee of , an apogee of , 65.9 degrees of inclination, and an orbital period of 95.2 minutes. It was used for a non-destructive intercept test, with both Kosmos 804 and Kosmos 814 intercepting it before deorbiting themselves. As of 2009, it is still in orbit. Kosmos 803 was the second of ten Lira satellites to be launched, of which all but the first were successful.

A minor anomaly during launch resulted in the satellite's orbit being slightly lower than had been planned, with its orbital period being 22.8 seconds shorter than the target orbit. Despite this the satellite performed its mission successfully. The satellite also carried a science package. Kosmos 143 was operated in a low Earth orbit, at an epoch of 27 February 1967, it had a perigee of , an apogee of , an inclination of 65.0°, and an orbital period of 89.5 minutes.

After liftoff, Chang'e 1 made three orbits around the Earth, a burn at perigee extending the orbit's apogee further each time, until a final translunar injection burn placed it on course for the Moon on October 31, 2007. Another burn placed it in a polar orbit around the Moon, with burns at the periselenium of the first three orbits decreasing the aposelenium until it entered a final circular orbit. Lunar orbit insertion was achieved on the November 5, 2007.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1971-101A. The North American Aerospace Defense Command assigned it the catalogue number 05623. Kosmos 458 was the forty-eighth of seventy nine DS-P1-Yu satellites to be launched, and the forty-third of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.9 minutes.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1971-113A. The North American Aerospace Defense Command assigned it the catalogue number 05704. Kosmos 467 was the forty-ninth of seventy nine DS-P1-Yu satellites to be launched, and the forty-fourth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.7 minutes.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1972-004A. The North American Aerospace Defense Command assigned it the catalogue number 05804. Kosmos 472 was the fiftieth of seventy nine DS-P1-Yu satellites to be launched, and the forty-fifth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 81.9 degrees of inclination, and an orbital period of 101 minutes.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1972-020A. The North American Aerospace Defense Command assigned it the catalogue number 05906. Kosmos 481 was the fifty-first of seventy nine DS-P1-Yu satellites to be launched, and the forty-sixth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 92 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1973-091A. The North American Aerospace Defense Command assigned it the catalogue number 06941. Kosmos 608 was the sixty-sixth of seventy nine DS-P1-Yu satellites to be launched, and the sixtieth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 92.1 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1973-004A. The North American Aerospace Defense Command assigned it the catalogue number 06348. Kosmos 545 was the sixtieth of seventy nine DS-P1-Yu satellites to be launched, and the fifty- fourth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.9 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1975-058A. The North American Aerospace Defense Command assigned it the catalogue number 07982. Kosmos 745 was the seventy-seventh of seventy nine DS-P1-Yu satellites to be launched, and the seventieth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 92.1 minutes.

A circular orbit is a special case, wherein the foci of the ellipse coincide. The point where the orbiting body is closest to Earth is called the perigee, and is called the periapsis (less properly, "perifocus" or "pericentron") when the orbit is about a body other than Earth. The point where the satellite is farthest from Earth is called the apogee, apoapsis, or sometimes apifocus or apocentron. A line drawn from periapsis to apoapsis is the line-of-apsides.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1976-044A. The North American Aerospace Defense Command assigned it the catalogue number 08851. Kosmos 818 was the seventy-eighth and penultimate DS-P1-Yu satellite to be launched, and the seventy-first to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 91.9 minutes.

It was the final flight of the Kosmos-2I carrier rocket, and the final flight of an R-12 family rocket. Kosmos launches continued using the R-14-derived Kosmos-3M. It also marked the last launch from Plesetsk Site 133/1 until it was rebuilt as Site 133/3 in 1985. Kosmos 919 was placed into a low Earth orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 95.6 minutes.

Kosmos 394 was placed into a low Earth orbit with a perigee of , an apogee of , 65.8 degrees of inclination, and an orbital period of 95.4 minutes. As of 2009, debris from its destruction is still in orbit. Kosmos 394 was the second of the five original DS-P1-M satellites to be launched, and the first to successfully reach orbit. The three subsequent launches were all successful, before the satellite was replaced with a derivative, Lira.

EDUSAT was successfully launched into a Geosynchronous Transfer Orbit (GTO) on the first operational launch of the Geosynchronous Satellite Launch Vehicle, which flew from the First Launch Pad at the Satish Dhawan Space Centre in Sriharikota. EDUSAT was initially placed into a transfer orbit with a perigee of and an apogee of and a period of 10.5 hours, inclined at 19.2 degrees to the equator. EDUSAT was decommissioned in September 2010 and relocated to a graveyard orbit.

As of 12 March 2016, USA-266 was in an orbit with a perigee of , an apogee of , a period of 717.9 minutes, and 55.01 degrees of inclination to the equator. It is used to broadcast the PRN 32 signal, and operates in slot 5 of plane F of the GPS constellation. The satellite has a design life of 15 years and a mass of . It is currently in service following commissioning on March 9, 2016.

Kosmos 1805 was launched at 07:30 UTC on December 10, 1986 atop a Tsyklon-3 rocket flying from Site 32/2 at the Plesetsk Cosmodrome. Following its successful launch, the satellite was given its Kosmos designation, along with international designator 1986-097A, and Satellite Catalog Number 17191. By 9 January 1987, the satellite was in an orbit with a perigee of , an apogee of , 82.5 degrees of inclination, and an orbital period of 97.68 minutes.

An Atlas LV-3A Agena-A rocket was used, flying from Launch Complex 1-1 at the Point Arguello Naval Air Station. Ten minutes and fourteen seconds later, the Agena's engine cut off, having successfully achieved a low Earth orbit. It was assigned the Harvard designation 1961 Alpha 1. Samos 2 operated in a Sun-synchronous low Earth orbit, with an apogee of , a perigee of , an inclination of 97.4 degrees, and a period of 94.9 minutes.

Maneuvers to move the satellite into its designated geosynchronous orbit at 83 degrees East longitude were initiated on 28 August 2015 by firing motors on board the GSAT-6 satellite. The GSAT-6 satellite's Liquid Apogee Motor (LAM) was fired for 3385 seconds at 08:35 hours IST on August 28 during the first orbit raising operation and modified the satellite orbit to 8,408 km (perigee height) by 35,708 km (apogee height) with an inclination of 7.5 degree and an orbital period of 13 hours, 15 minutes and 24 seconds. Second orbit raising operation of GSAT-6 was successfully completed by firing the Apogee Motor for 2663 seconds at 11:10:53 hours IST on Aug 29, 2015. Realized orbit was 26,998 km (perigee height) by 35,682 km (apogee height) with an inclination of 0.115 degree and an orbital period of 20 hours and 15 minutes. Third orbit raising operation of GSAT-6 was successfully completed by firing the Apogee Motor for 580.32 seconds at 07:46 hours IST on Aug 30, 2015.

Intelsat 29e, its only passenger, separated 30 minutes later, and the satellite first signals were received shortly afterwards by the Kumsan, South Korea, Ground Station. The next two days were spent evaluating the health of the satellite and determining the exact orbit, then a series of nine orbital maneuvers to raise the perigee to were started. This orbit circularization would consume approximately of propellant. When it reached its test position at 49.7° West, it deployed its antennas and solar panels.

Kosmos 268 was launched from Site 86/4 at Kapustin Yar, atop a Kosmos-2I 63SM carrier rocket. The launch occurred on 5 March 1969 at 13:04:55 UTC, and resulted in Kosmos 268's successful deployment into low Earth orbit. Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1969-020A. Kosmos 268 was operated in an orbit with a perigee of , an apogee of , 48.4 degrees of inclination, and an orbital period of 108 minutes.

During STS-51-D, the shuttle crew deployed two communications satellites: Telesat-I (Anik C1) and Syncom IV-3 (also known as Leasat-3). Telesat-I was attached to a Payload Assist Module (PAM-D) motor and successfully deployed. Syncom IV-3, however, failed to initiate antenna deployment and spin-up, or ignite its perigee kick motor upon deployment. The mission was consequently extended by two days to ensure that the satellite's spacecraft sequencer start lever was in its proper position.

Upon successfully reaching orbit, it was assigned the Harvard designation 1961 Alpha Zeta 1. Discoverer 35 was operated in a low Earth orbit, with a perigee of , an apogee of , 81.6 degrees of inclination, and a period of 89.3 minutes. The satellite had a mass of , and was equipped with a panoramic camera with a focal length of , which had a maximum resolution of . Images were recorded onto film, and returned in a Satellite Recovery Vehicle just over a day after launch.

Upon successfully reaching orbit, it was assigned the Harvard designation 1961 Alpha Gamma 1. Discoverer 32 was operated in a low Earth orbit, with a perigee of , an apogee of , 81.6 degrees of inclination, and a period of 90.3 minutes. The satellite had a mass of , and was equipped with a panoramic camera with a focal length of , which had a maximum resolution of . Images were recorded onto film, and returned in a Satellite Recovery Vehicle, which was deorbited one day after launch.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1967-086A. Kosmos 176 was operated in an orbit with a perigee of , an apogee of , an inclination of 81.9°, and an orbital period of 102.5 minutes. It remained in orbit until it decayed and reentered the atmosphere on 3 March 1968. It was the tenth of seventy nine DS-P1-Yu satellites to be launched, and the ninth of seventy two to successfully reach orbit.

On this engine, one of those seams had failed during a static firing, and despite subsequent repair, it was suspected that the same seam had failed again. The orbit of the Orion 3 satellite was raised slightly, and its inclination reduced, using onboard propulsion. It was left in an orbit with a perigee of , an apogee of , and 29° inclination. Its operators received US$247 million in insurance for the loss of the satellite, which was turned over to its insurers.

Upon successfully reaching orbit, it was assigned the Harvard designation 1961 Pi 1. Discoverer 26 was operated in a low Earth orbit, with a perigee of , an apogee of , 82.9 degrees of inclination, and a period of 94 minutes. The satellite had a mass of , and was equipped with a panoramic camera with a focal length of , which had a maximum resolution of . Images were recorded onto film, and returned in a Satellite Recovery Vehicle, which was deorbited two days after launch.

A debris cloud resulting from a single event is studied with scatter plots known as Gabbard diagrams, where the perigee and apogee of fragments are plotted with respect to their orbital period. Gabbard diagrams of the early debris cloud prior to the effects of perturbations, if the data were available, are reconstructed. They often include data on newly observed, as yet uncatalogued fragments. Gabbard diagrams can provide important insights into the features of the fragmentation, the direction and point of impact.

The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 10 November 1999, USA-145 was in an orbit with a perigee of , an apogee of , a period of 717.96 minutes, and 53 degrees of inclination to the equator. It is used to broadcast the PRN 11 signal, and operated in slot 2 of plane D of the GPS constellation; however, it had been moved to slot 5 by 2011, with USA-71 covering slot 2.

Upon successfully reaching orbit, it was assigned the Harvard designation 1961 Alpha Beta 1. Discoverer 31 was operated in a low Earth orbit, with a perigee of , an apogee of , 82.7 degrees of inclination, and a period of 90.7 minutes. The satellite had a mass of , and was equipped with a panoramic camera with a focal length of , which had a maximum resolution of . Images were recorded onto film, and were to have been returned in a Satellite Recovery Vehicle.

Monument to Paul de Vivie Vélocio at the summit of the col At the top is a monument in memory of Paul de Vivie, who wrote under the pseudonym Vélocio and was important in the development of bicycle touring. The col de la République was his favourite morning ride.Peter Nye, The Cyclist's Sourcebook, New York: Perigee, 1991, , p. 100.John Krausz, Vera van der Reis Krausz, and Paul Harris, The Bicycling Book: Transportation, Recreation, Sport, New York: Dial, 1982, , p. 68.

On 9 November 2013, a published report indicated that the satellite was expected to re-enter within a day or two. By this date, the perigee altitude had decayed to . On 10 November, ESA expected re-entry to occur between 18:30 and 24:00 UTC that day, with the most probable impact ground swath largely running over ocean and polar regions. Its descending orbit on 11 November 2013 passed over Siberia, the western Pacific Ocean, the eastern Indian Ocean and Antarctica.

This venting also maintained safe pressures as liquid hydrogen boiled off in the fuel tank. This venting thrust easily exceeded aerodynamic drag. For the final three Apollo flights, the temporary parking orbit was even lower (approximately ), to increase payload for these missions. The Apollo 9 Earth orbit mission was launched into the nominal orbit consistent with Apollo 11, but the spacecraft were able to use their own engines to raise the perigee high enough to sustain the 10-day mission.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1971-037A. Kosmos 408 was the forty-first of seventy nine DS-P1-Yu satellites to be launched, and the thirty-seventh of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 81.8 degrees of inclination, and an orbital period of 100.66 minutes. It remained in orbit until it decayed and reentered the atmosphere on 29 December 1971.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1971-044A. Kosmos 421 was the forty-second of seventy nine DS-P1-Yu satellites to be launched, and the thirty-eighth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.65 minutes. It remained in orbit until it decayed and reentered the atmosphere on 8 November 1971.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1971-007A. Kosmos 393 was the thirty-ninth of seventy nine DS-P1-Yu satellites to be launched, and the thirty-sixth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 91.7 minutes. It remained in orbit until it decayed and reentered the atmosphere on 16 June 1971.

SDS satellites have a highly elliptical orbit, going from about 300 kilometers at perigee to roughly 39,000 km at apogee in order to allow communications with polar stations that cannot contact geosynchronous satellites. The high apogee meant that the polar regions were visible for long amounts of time, and only two satellites were required in order to achieve constant communications ability. In addition, two geostationary satellites appear to be part of the system. The SDS satellites were constructed by Hughes Aircraft.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1969-049A. Kosmos 285 was operated in an orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 91.6 minutes. It remained in orbit until it decayed and reentered the atmosphere on 7 October 1969. It was the twenty-second of seventy nine DS-P1-Yu satellites to be launched, and the twenty-first of seventy two to successfully reach orbit.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1969-047A. Kosmos 283 was operated in an orbit with a perigee of , an apogee of , 81.9 degrees of inclination, and an orbital period of 100.5 minutes. It remained in orbit until it decayed and reentered the atmosphere on 10 December 1969. It was the twenty-first of seventy nine DS-P1-Yu satellites to be launched, and the twentieth of seventy two to successfully reach orbit.

Onboard cameras were used to establish the attitude of the satellite, and the magnetorquer system was used to spin- stabilize the satellite. During June 2001, gas from the arcjet thruster was vented during apogee to raise perigee and stabilize the orbit of the satellite. Because of issues with the initial 400N burn, the apogee of the spacecraft was considerably higher than initially designed, but this was not a major issue. Subsequently, the communication packages and cameras were gradually re-activated.

Soap Opera Babylon, Perigee Trade, 1987—to ask Katzman to return to the show in his old capacity. Katzman agreed, reportedly under the condition that he would have "total authority" on the show, and as of the tenth season premiere he was promoted to executive producer, and Capice was let go. Katzman remained as executive producer on Dallas until the series finale in May 1991. Besides his production work, he also wrote and directed more episodes of the series than anyone else.

USA-221 is a spacecraft, measuring by by . It operates in a low Earth orbit with an apogee of , a perigee of , and 72 degrees of orbital inclination. The Space Plasma Characterization Source (SPCS) studies how a cold gas ammonia thruster and a Hall effect thruster behave in space, and how they affect the spacecraft's surroundings. Meanwhile, the Wafer- Integrated Spectrometer, WISPERS, will observe the plume generated by the Hall thruster, allowing a comparison to be made to theoretical data.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1968-056A. The North American Air Defense Command assigned it the catalogue number 03308. Kosmos 230 was the second of two DS-U3-S satellites to be launched, after Kosmos 166. It was operated in an orbit with a perigee of , an apogee of , an inclination of 48.5°, and an orbital period of 93.0 minutes, until decaying from orbit and reentering the atmosphere on 2 November 1968.

It was described by observers as "special for its colours around the horizon. There were wonderful oranges and reds all around, the clouds lit up, some dark in silhouette, some golden, glowing yellowy-orange in the distance. You could see the shadow approaching against the clouds and then rushing away as it left."Dr John Mason describing the eclipse directly after observing it The moon's apparent diameter was larger because the eclipse was occurring only 58 hours, 56 minutes after perigee.

The Diggers took their name from the original English Diggers led by Gerrard Winstanley and sought to create a mini-society free of money and capitalism. On the other hand, the Yippies employed theatrical gestures, such as advancing a pig ("Pigasus the Immortal") as a candidate for President in 1968, to mock the social status quo. They have been described as a highly theatrical, anti-authoritarian and anarchistAbbie Hoffman, Soon to be a Major Motion Picture, page 128. Perigee Books, 1980.

The probe was the first dedicated 3MV spacecraft that the Soviets launched (earlier missions had been of the test "Object-Probe" versions as Kosmos 21). It was designed to accomplish atmospheric entry into Venus followed by descent and impact. On 27 March 1964, it had a perigee of and an apogee of , with an inclination of 64.8° and an orbital period of 88.7 minutes. The spacecraft successfully reached Earth orbit but failed to leave for Venus when the Blok L upper stage malfunctioned.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1971-047A. Kosmos 423 was the forty-third of seventy nine DS-P1-Yu satellites to be launched, and the thirty-ninth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 91.8 minutes. It remained in orbit until it decayed and reentered the atmosphere on 26 November 1971.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1971-072A. Kosmos 435 was the forty-fifth of seventy nine DS-P1-Yu satellites to be launched, and the fortieth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.8 minutes. It remained in orbit until it decayed and reentered the atmosphere on 28 January 1972.

Kosmos 147 was operated in a low Earth orbit, at an epoch of 13 March 1967, it had a perigee of , an apogee of , an inclination of 65.0°, and an orbital period of 89.5 minutes. After eight days in orbit, Kosmos 147 was deorbited, with its return capsule descending under parachute and landing at 06:29 GMT on 21 March 1967, and recovered by the Soviet forces. An unspecified problem with the satellite resulted in the mission being considered a partial failure.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1971-090A. Kosmos 453 was the forty-sixth of seventy nine DS-P1-Yu satellites to be launched, and the forty-first of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.9 minutes. It remained in orbit until it decayed and reentered the atmosphere on 19 March 1972.

Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1971-097A. Kosmos 455 was the forty-seventh of seventy nine DS-P1-Yu satellites to be launched, and the forty-second of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.9 minutes. It remained in orbit until it decayed and reentered the atmosphere on 9 April 1972.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1972-028A. The North American Aerospace Defense Command assigned it the catalogue number 05938. Kosmos 485 was the fifty-second of seventy nine DS-P1-Yu satellites to be launched, and the forty-seventh of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.6 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1972-033A. The North American Aerospace Defense Command assigned it the catalogue number 06006. Kosmos 487 was the fifty-third of seventy nine DS-P1-Yu satellites to be launched, and the forty-eighth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.8 minutes.

The largest possible apparent diameter of the Moon is the same 12% larger (as perigee versus apogee distances) than the smallest; the apparent area is 25% more and so is the amount of light it reflects toward Earth. The variance in the Moon's orbital distance corresponds with changes in its tangential and angular speeds, as stated in Kepler's second law. The mean angular movement relative to an imaginary observer at the Earth–Moon barycentre is ° per day to the east (J2000.0 epoch).

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1973-075A. The North American Aerospace Defense Command assigned it the catalogue number 06875. Kosmos 601 was the sixty-fifth of seventy nine DS-P1-Yu satellites to be launched, and the fifty- ninth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 81.8 degrees of inclination, and an orbital period of 100.9 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1972-078A. The North American Aerospace Defense Command assigned it the catalogue number 06222. Kosmos 523 was the fifty-seventh of seventy nine DS-P1-Yu satellites to be launched, and the fifty-first of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 91.7 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1973-094A. The North American Aerospace Defense Command assigned it the catalogue number 06952. Kosmos 611 was the sixty-seventh of seventy nine DS-P1-Yu satellites to be launched, and the sixty-first of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.8 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1974-010A. The North American Aerospace Defense Command assigned it the catalogue number 07187. Kosmos 633 was the sixty-eighth of seventy nine DS-P1-Yu satellites to be launched, and the sixty-second of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.9 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1974-012A. The North American Aerospace Defense Command assigned it the catalogue number 07211. Kosmos 634 was the sixty-ninth of seventy nine DS-P1-Yu satellites to be launched, and the sixty-third of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.9 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1972-080A. The North American Aerospace Defense Command assigned it the catalogue number 06229. Kosmos 524 was the fifty-eighth of seventy nine DS-P1-Yu satellites to be launched, and the fifty-second of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.9 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1972-084A. The North American Aerospace Defense Command assigned it the catalogue number 06254. Kosmos 526 was the fifty-ninth of seventy nine DS-P1-Yu satellites to be launched, and the fifty-third of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.8 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1973-035A. The North American Aerospace Defense Command assigned it the catalogue number 06665. Kosmos 562 was the sixty-third of seventy nine DS-P1-Yu satellites to be launched, and the fifty- seventh of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.9 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1973-057A. The North American Aerospace Defense Command assigned it the catalogue number 06793. Kosmos 580 was the sixty-fourth of seventy nine DS-P1-Yu satellites to be launched, and the fifty-eighth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 91.9 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1973-020A. The North American Aerospace Defense Command assigned it the catalogue number 06427. Kosmos 553 was the sixty-first of seventy nine DS-P1-Yu satellites to be launched, and the fifty- fifth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.9 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1973-029A. The North American Aerospace Defense Command assigned it the catalogue number 06645. Kosmos 558 was the sixty-second of seventy nine DS-P1-Yu satellites to be launched, and the fifty-sixth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 92 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1972-050A. The North American Aerospace Defense Command assigned it the catalogue number 06086. Kosmos 498 was the fifty-fifth of seventy nine DS-P1-Yu satellites to be launched, and the forty-ninth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.8 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1974-058A. The North American Aerospace Defense Command assigned it the catalogue number 07385. Kosmos 668 was the seventy-first of seventy nine DS-P1-Yu satellites to be launched, and the sixty-fourth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 92 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1974-074A. The North American Aerospace Defense Command assigned it the catalogue number 07447. Kosmos 686 was the seventy-second of seventy nine DS-P1-Yu satellites to be launched, and the sixty-fifth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.8 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1974-091A. The North American Aerospace Defense Command assigned it the catalogue number 07538. Kosmos 695 was the seventy-third of seventy nine DS-P1-Yu satellites to be launched, and the sixty-sixth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.7 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1975-003A. The North American Aerospace Defense Command assigned it the catalogue number 07611. Kosmos 703 was the seventy-fourth of seventy nine DS-P1-Yu satellites to be launched, and the sixty-seventh of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 81.9 degrees of inclination, and an orbital period of 101.2 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1975-006A. The North American Aerospace Defense Command assigned it the catalogue number 07623. Kosmos 705 was the seventy-fifth of seventy nine DS-P1-Yu satellites to be launched, and the sixty-eighth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 92.1 minutes.

Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1975-026A. The North American Aerospace Defense Command assigned it the catalogue number 07730. Kosmos 725 was the seventy-sixth of seventy nine DS-P1-Yu satellites to be launched, and the sixty-ninth of seventy two to successfully reach orbit. It was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.9 minutes.

The orbit has evolved over time; the line of apsides has rotated southwards so that the distance at which the orbit crossed the magnetotail current sheet progressively reduced, and a wide range of dayside magnetopause crossing latitudes were sampled. Gravitational effects impose a long term cycle of change in the perigee (and apogee) distance, which saw the perigees reduce to a few 100 km in 2011 before beginning to rise again. The orbit plane has rotated away from 90 degrees inclination.

Kosmos 459 was placed into a low Earth orbit with a perigee of , an apogee of , 65 degrees of inclination, and an orbital period of 89.4 minutes. It was successfully intercepted and destroyed by Kosmos 462. Two major pieces of debris were associated with the satellite, which decayed from orbit on 1 and 7 December 1971. Kosmos 459 was the fourth of the five original DS-P1-M satellites to be launched, of which all but the first successfully reached orbit.

The Biosatellite 1 was the first series Biosatellite satellites. It was inserted in an initial orbit of 296 km perigee, 309 km apogee and 33.5 degrees of orbital inclination, with a period 90.5 minutes. The Biosatellite 1 was carrying several specimens for the study of the effects of the space environment on biological processes. When the capsule was returning to land, it separated from the vehicle properly, but its rocket motor did not work, leaving it stranded in a slowly decaying orbit.

Explorer 24 was placed in orbit together with Explorer 25 from a single launch vehicle. Explorer 24 was identical in configuration to the previously launched balloon satellites Explorer 9 and 19. The spacecraft was 3.6 m in diameter, was built of alternating layers of aluminum foil and plastic film, and was covered uniformly with 5.1-cm white dots for thermal control. It was designed to yield atmospheric density near perigee as a function of space and time from sequential observations of the sphere's position in orbit.

This was only the second time the Delta booster had failed, and the incident followed 22 prior successes. A second S-66 was launched, this time successfully, via a Scout X-4 rocket at 03:01 UT, October 9, 1964, from the PALC-D launch facility at Vandenberg Air Force Base. Once in space, it became known as Explorer 22. Explorer 22 had a nearly polar orbit, inclined 79.7° to the equator, with an initial apogee of and perigee of , and a period of 104.7 minutes.

Kosmos 277 was launched from Site 133/1 at the Plesetsk Cosmodrome, atop a Kosmos-2I 63SM carrier rocket. The launch occurred on 4 April 1969 at 13:00:04 UTC, and resulted in Kosmos 277's successful deployment into low Earth orbit. Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1969-033A. Kosmos 277 was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.2 minutes.

On October 9, the satellite was mated in the lower berth of the launch vehicle. On October 16, 2014 at 21:43:52hs UTC, ARSAT-1 was successfully launched from the Guiana Space Centre ELA-3 by an Ariane-5ECA on its VA220 flight. It flew along the Intelsat 30 which rode on the top berth of the fairing. Two days later, on October 18, it performed the first of five orbital maneuvers using its LAE to increase the perigee to and reduced the inclination to 3.5°.

Following its successful arrival in orbit the spacecraft received its Kosmos designation; along with the International Designator 1965-103A and the Satellite Catalog Number 01817. Kosmos 99 was operated in a low Earth orbit, at an epoch of 10 December 1965, it had a perigee of , an apogee of , an inclination of 65.0° and an orbital period of 89.6 minutes. On 18 December 1965, after eight days in orbit, the satellite was deorbited with its return capsule descending by parachute for recovery by the Soviet force.

Although the satellite achieved orbit, and was assigned the Harvard designation 1961 Alpha Epsilon 1, the launch was unsuccessful. An anomalous angle taken during ascent resulted in the spacecraft being placed into an unusable orbit. It was the second consecutive KH-3 launch failure; the previous mission, Discoverer 33, had failed to achieve orbit due to a separation failure. Discoverer 34 was launched into a low Earth orbit, with a perigee of , an apogee of , 82.5 degrees of inclination, and a period of 96.6 minutes.

Following deployment from Challenger, TDRS-1 was to be raised to its operational geosynchronous orbit by means of an Inertial Upper Stage, which consisted of two solid rocket motors, the first used to raise the orbit's apogee, the second its perigee. The first burn was successful, however the IUS went out of control during the second burn. TDRS-1 separated from the upper stage in a lower than planned orbit. It was eventually raised to geosynchronous orbit by means of its attitude control system.

Lasers are designed to target debris between one and ten centimeters in diameter. Collisions with such debris are commonly of such high velocity that considerable damage and numerous secondary fragments are the result. The laser broom is intended to be used at high enough power to penetrate through the atmosphere with enough remaining power to ablate material from the target. The ablating material imparts a small thrust that lowers its orbital perigee into the upper atmosphere, thereby increasing drag so that its remaining orbital life is short.

On 17 March 1958, the three-stage launch vehicle placed Vanguard into a 654 x 3969 kilometers, 134.2 minute elliptical orbit inclined at 34.25°. Original estimates had the orbit lasting for 2,000 years, but it was discovered that solar radiation pressure and atmospheric drag during high levels of solar activity produced significant perturbations in the perigee height of the satellite, which caused a significant decrease in its expected lifetime to about 240 years. Vanguard 1 transmitted its signals for nearly seven years as it orbited the Earth.

During this mission, the third and fourth stages separated abnormally, and after reaching Earth orbit, ground control lost telemetry (at 06:45:44 GMT) from the Blok L upper stage designed to send the vehicle past the Moon. As a result, the spacecraft remained stranded in Earth orbit. The main engine turbopump of stage probably exploded upon ignition destroying the spacecraft. On 11 November 1963, it had a perigee of and an apogee of , with an inclination of 64.8°, and an orbital period of 88.5 minutes.

Every two years, low-energy transfer windows open up, which allow movement between planets with the lowest possible energy requirements. Transfer injections can place spacecraft into either a Hohmann transfer orbit or bi-elliptic transfer orbit. Trans-Mars injections can be either a single maneuver burn, such as that used by the NASA MAVEN orbiter in 2013, or a series of perigee kicks, such as that used by the ISRO Mars Orbiter Mission in 2013.ISRO successfully sends Mars orbiter into sun-centric orbit.

Discoverer 23 was operated in an Earth orbit, with a perigee of , an apogee of , 82.3° of inclination, and a period of 93.77 minutes. The satellite had a mass of , and was equipped with a frame camera with a focal length of , which had a maximum resolution of . Images were recorded onto film, and ejected aboard a Satellite Return Vehicle, SRV-521. Due to a problem with Discoverer 23's attitude control system, the SRV ended up boosting itself into a higher orbit rather than deorbiting.

After the launch with a Japanese satellite launcher and a 7-day orbital flight, the landing of the EXPRESS capsule was planned to occur in the vicinity of the town of Coober Pedy (Australia). However, due to a malfunction of the rocket, the capsule entered an elliptical orbit with very low Perigee and landed in Africa after only a few revolutions. Further applications of developments of MORABA in space flight missions included experiments aboard the Russian space station Mir and the DLR satellite BIRD.

Kosmos 295 was launched from Site 133/1 at the Plesetsk Cosmodrome, atop a Kosmos-2I 63SM carrier rocket. The launch occurred on 22 August 1969 at 14:14:57 UTC, and resulted in Kosmos 295's successful deployment into low Earth orbit. Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1969-073A. Kosmos 295 was operated in an orbit with a perigee of , an apogee of , 70.9 degrees of inclination, and an orbital period of 91.5 minutes.

Kosmos 303 was launched from Site 133/1 at the Plesetsk Cosmodrome, atop a Kosmos-2I 63SM carrier rocket. The launch occurred on 18 October 1969 at 10:00:03 UTC, and resulted in the successful deployment of Kosmos 303 into low Earth orbit. Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1969-090A. Kosmos 303 was operated in an orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 91.4 minutes.

Kosmos 314 was launched from Site 133/1 at the Plesetsk Cosmodrome, atop a Kosmos-2I 63SM carrier rocket. The launch occurred on 11 December 1969 at 12:58:59 UTC, and resulted in the successful deployment of Kosmos 314 into low Earth orbit. Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1969-106A. Kosmos 314 was operated in an orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 91.4 minutes.

Kosmos 307 was launched from Site 86/4 at Kapustin Yar, atop a Kosmos-2I 63SM carrier rocket. The launch occurred on 24 October 1969 at 13:01:58 UTC, and resulted in the successful deployment of Kosmos 307 into low Earth orbit. Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1969-094A. Kosmos 307 was operated in an orbit with a perigee of , an apogee of , 48.4 degrees of inclination, and an orbital period of 107.7 minutes.

Kosmos 311 was launched from Site 133/1 at the Plesetsk Cosmodrome, atop a Kosmos-2I 63SM carrier rocket. The launch occurred on 24 November 1969 at 11:00:04 UTC, and resulted in the successful deployment of Kosmos 311 into low Earth orbit. Upon reaching orbit, it was assigned its Kosmos designation, and received the International Designator 1969-102A. Kosmos 311 was operated in an orbit with a perigee of , an apogee of , 71 degrees of inclination, and an orbital period of 91.5 minutes.

Fig. 1: Diagram of orbital elements, including the argument of periapsis (ω). The argument of periapsis (also called argument of perifocus or argument of pericenter), symbolized as ω, is one of the orbital elements of an orbiting body. Parametrically, ω is the angle from the body's ascending node to its periapsis, measured in the direction of motion. For specific types of orbits, words such as perihelion (for heliocentric orbits), perigee (for geocentric orbits), periastron (for orbits around stars), and so on may replace the word periapsis.

INSAT 3E was launched from Kourou, French Guyana on September 28, 2003 on European consortium Ariane space's Ariane 5-V162 launcher along with two other satellites viz. Eurobird 3 of Eutelsat and SMART-1 of European Space Agency at 4.44 am IST.It was placed into a Geosynchronous Transfer Orbit (GTO) 30 minutes after the lift-off, in 3-axis stabilised mode, with a perigee of 649 km and an apogee of 35,923 km and an inclination of 7 deg. with respect to the equator.

INSAT 3A was launched by Ariane-5 launch vehicle of Arianespace on April 9, 2003 at 22.52 UTC from Kourou, French Guiana. It was placed into a Geosynchronous Transfer Orbit (GTO), 30 minutes after the lift-off in 3-axis stabilized mode, with a perigee (nearest point to earth) of 859 km and an apogee (farthest point to earth) of 36,055 km and an inclination of 1.99 deg. with respect to the equator. Its co-passenger on its launch was GALAXI-XII of PanAmSat.

The operational orbit would last at least nine years, with the RadioAstron never being in the Earth's shadow for more than two hours. With its apogee as far as the orbit of the Moon, Spektr-R could be considered a deep-space mission. In fact, the gravitational pull of the Moon was expected to fluctuate the satellite's orbit in three-year cycles, with its apogee travelling between 265,000 and from Earth and its perigee between . Each orbit would take RadioAstron around eight to nine days.

The spacecraft was deployed into a low Earth orbit with a perigee of , an apogee of , an 51.9° of inclination, and an orbital period of 89.8 minutes. The spacecraft was named Kosmos 96, part of a series typically used for military and experimental satellites in order to cover up the failure. Had it departed Earth's orbit, it would have received the next designation in the Venera series, at the time Venera 4. Kosmos 96 was destroyed when it re-entered the Earth's atmosphere on 9 December 1965.

Kosmos 909 was placed into a low Earth orbit with a perigee of , an apogee of , 65.9 degrees of inclination, and an orbital period of 117 minutes. Attempted interceptions by Kosmos 910 and 918 on 23 May and 17 June respectively failed, and as of 2009 Kosmos 909 remains in orbit. Kosmos 909 was the fifth of ten Lira satellites to be launched, of which all but the first were successful. Lira was derived from the earlier DS-P1-M satellite, which it replaced.

The satellite reached a slightly lower orbit than had been planned, but was still able to complete its mission. Kosmos 138 was operated in a low Earth orbit, at an epoch of 19 January 1967, it had a perigee of , an apogee of , an inclination of 65.0°, and an orbital period of 89.2 minutes. After 8 days in orbit, Kosmos 138 was deorbited, with its return capsule descending under parachute, landing at 06:14 GMT on 27 January 1967, and recovered by Soviet force.

The launch took place on 6 October at 07:12 GMT from Gagarin's Start, Site 1/5 at Baikonur Cosmodrome onboard a Voskhod rocket s/n R15000-02. Kosmos 47 was operated in a low Earth orbit, it had a perigee of , an apogee of , an inclination of 64.8° and an orbital period of 90.0 minutes. On 7 October 1964, testing of all the spacecraft's systems occurred in the space of 24 hours. The landing took place on 7 October 1964 at around 07:30 GMT.

It has a metallicity of −0.06, which means that the abundance of elements other than hydrogen and helium is just 87.1% that of the Sun. This is a high proper motion star that moves about 0.77 arcseconds per year relative to background stars. In physical terms it is travelling with a space velocity of 31.1 km/s relative to the Solar System. The galactic orbit of this star carries it 21,300 ly from the Galactic Center at its perigee to 30,600 ly at its apogee.

It was designed, built, and tracked by personnel at the Department of Physics and Astronomy, University of Iowa whose sports teams are the Hawkeyes. The spacecraft was launched on June 3, 1974 into a polar orbit with initial apogee over the North Pole and re-entered on April 28, 1978 after 667 orbits or nearly four years of continuous operation. The spacecraft apogee was between 20.28 and 20.92 Earth radii with less than a 1.7 Earth radii perigee. The orbital period was 51.3 hours.

Perigee (closest approach to the Earth) was 15 January 2007, at a distance of 0.82 AU. After passing the Sun, McNaught became visible in the Southern Hemisphere. In Australia, according to Siding Spring Observatory at Coonabarabran, where the comet was discovered, it was to have reached its theoretical peak in brightness on Sunday 14 January just after sunset, when it would have been visible for 23 minutes. On 15 January the comet was observed at Perth Observatory with an estimated apparent magnitude of −4.0.

It was visible across the Pacific ocean, southern Costa Rica, northern Nicaragua and San Andrés Island, Colombia. The central shadow passed just south of Hawaii in early morning and ended over Central America near sunset. This is the first solar eclipse to occur since the September 11, 2001 attacks. The moon's apparent diameter was near the average diameter because the eclipse occurred 7.9 days after perigee (December 6, 2001 at 22:49 UTC) and 6.7 days before apogee (December 21, 2001 at 13:03 UTC).

In 2009, Perigee (a division of Penguin Books) published La Carmina's Cute Yummy Time, a cookbook based on Japanese "charaben" ("character bento"), a style of bento in which food is decorated to resemble animals, cartoon characters, and other such figures. She took all the photos and drew illustrations for the book. La Carmina's promotional tour included book signings in US cities and an appearance on The Today Show. The Guardian named Cute Yummy Time as one of the oddest book titles of the year, and the Washington Post recommended it in Gift Guide.

Adoption: The Essential Guide to Adopting Quickly and Safely, by Randall Hicks, Perigee Press 2007 After the dossier is reviewed and the prospective parents are approved to adopt, they are matched to an eligible child (except in some countries such as India, which does not allow "matching" of a child to (a) prospective parent(s)). The parent is usually sent information about the child, such as age, gender, health history, etc. This is generally called a referral. A travel date is typically provided at a later time in most adoptions.

Maximum (instantaneous) orbital speed occurs at periapsis (perigee, perihelion, etc.), while minimum speed for objects in closed orbits occurs at apoapsis (apogee, aphelion, etc.). In ideal two-body systems, objects in open orbits continue to slow down forever as their distance to the barycenter increases. When a system approximates a two-body system, instantaneous orbital speed at a given point of the orbit can be computed from its distance to the central body and the object's specific orbital energy, sometimes called "total energy". Specific orbital energy is constant and independent of position.

BILSAT-1 was launched from Plesetsk Cosmodrome Site 132/1, Arkhangelsk Oblast in Russia by a Kosmos-3M space launch vehicle on September 27, 2003 at 06:12 UTC in a multiple- satellite payload launch along with six other satellites, namely Mozhayets-4 and Larets of Russia, NigeriaSat-1 of Nigeria, UK-DMC from the United Kingdom, South Korean STSAT-1 and Germany's Rubin 4-DS. It was placed in a polar, circular, sun-synchronous geocentric orbit at an altitude of with orbital parameters as period 98.5 min, apogee , perigee and inclination 98.2°.

Lewis was launched by a LMLV-1 (Athena I) rocket flying from Space Launch Complex 6 at the Vandenberg Air Force Base. The launch was originally scheduled to take place in September 1996, but it was delayed due to technical problems affecting the rocket. Launch finally occurred at 06:51:01 GMT on 23 August 1997, and Lewis was successfully placed into a parking orbit with an apogee of , a perigee of , and 97.5 degrees of inclination. Lewis was to have raised itself into a higher orbit, at an altitude of .

Zooplankton in the Arctic use moonlight when the Sun is below the horizon for months on end. 14 November 2016 supermoon was away from the center of Earth, the closest occurrence since 26 January 1948. It will not be closer until 25 November 2034. The distance between the Moon and Earth varies from around to at perigee (closest) and apogee (farthest), respectively. On 14 November 2016, it was closer to Earth when at full phase than it has been since 1948, 14% closer than its farthest position in apogee.

Owing to the failure of the stabilisation boom, the backup sensor was not oriented in the correct direction, instead being oriented towards the moon, which overloaded it and shut down the sensor. The satellite exhausted its remaining propellant supply trying to regain earth- lock, and was abandoned on 6 September. Due to the sudden nature of its failure, INSAT-1A was not removed from geosynchronous orbit. As of 10 November 2013 it is in an orbit with a perigee of , an apogee of , inclination of 14.59 degrees and an orbital period of 23.93 hours.

Upon successfully reaching orbit, it was assigned the Harvard designation 1961 Psi 1. Discoverer 29 was operated in a low Earth orbit, with a perigee of , an apogee of , 82 degrees of inclination, and a period of 91 minutes. The satellite had a mass of , and was equipped with a panoramic camera with a focal length of , which had a maximum resolution of . Images were recorded onto film, and returned in a Satellite Recovery Vehicle two days after launch, but all of the images returned were found to be out of focus.

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 30 April 1990, USA-54 was in an orbit with a perigee of , an apogee of , a period of 717.84 minutes, and 55 degrees of inclination to the equator. The satellite had a mass of , and generated 710 watts of power. It had a design life of 7.5 years, however following problems with the satellite switching between timing standards, the satellite was declared unusable on 21 May 1996, and was decommissioned on 13 December.

The launch took place from Space Launch Complex 17A at the Cape Canaveral Air Force Station, and placed USA-199 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 15 February 2008, USA-199 was in an orbit with a perigee of , an apogee of , a period of 717.98 minutes, and 54.9 degrees of inclination to the equator. It is used to broadcast the PRN 29 signal, and operates in slot 1 of plane C of the GPS constellation.

The launch took place from Space Launch Complex 17A at the Cape Canaveral Air Force Station, and placed USA-196 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 27 October 2007, USA-196 was in an orbit with a perigee of , an apogee of , a period of 717.94 minutes, and 54.8 degrees of inclination to the equator. It is used to broadcast the PRN 15 signal, and operates in slot 2 of plane F of the GPS constellation.

The launch took place from Space Launch Complex 17B at the Cape Canaveral Air Force Station, and placed USA-177 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 20 May 2004, USA-177 was in an orbit with a perigee of , an apogee of , a period of 718 minutes, and 55 degrees of inclination to the equator. It is used to broadcast the PRN 19 signal, and operates in slot 3 of plane C of the GPS constellation.

The launch took place from Space Launch Complex 17B at the Cape Canaveral Air Force Station, and placed USA-178 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 23 August 2004, USA-178 was in an orbit with a perigee of , an apogee of , a period of 718 minutes, and 55 degrees of inclination to the equator. It is used to broadcast the PRN 23 signal, and operates in slot 4 of plane F of the GPS constellation.

The launch took place from Space Launch Complex 17B at the Cape Canaveral Air Force Station, and placed USA-180 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 5 January 2005, USA-180 was in an orbit with a perigee of , an apogee of , a period of 717.94 minutes, and 54.8 degrees of inclination to the equator. It is used to broadcast the PRN 02 signal, and operates in slot 1 of plane D of the GPS constellation.

The launch took place from Space Launch Complex 17A at the Cape Canaveral Air Force Station, and placed USA-183 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 25 November 2005, USA-183 was in an orbit with a perigee of , an apogee of , a period of 717.92 minutes, and 55 degrees of inclination to the equator. It is used to broadcast the PRN 17 signal, and operates in slot 4 of plane C of the GPS constellation.

The launch took place from Space Launch Complex 17A at the Cape Canaveral Air Force Station, and placed USA-154 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 13 November 2000, USA-154 was in an orbit with a perigee of , an apogee of , a period of 724.28 minutes, and 55 degrees of inclination to the equator. It was used to broadcast the PRN 14 signal, and operated in slot 5 of plane F of the GPS constellation.

The launch took place from Space Launch Complex 17A at the Cape Canaveral Air Force Station, and placed USA-156 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 2 February 2001, USA-156 was in an orbit with a perigee of , an apogee of , a period of 718.08 minutes, and 55 degrees of inclination to the equator. It is used to broadcast the PRN 18 signal, and operates in slot 4 of plane E of the GPS constellation.

The XSS-10 satellite was carried as a secondary payload on the same rocket, but was deployed from the second stage of the three-stage rocket. The launch took place from Space Launch Complex 17B at the Cape Canaveral Air Force Station, and placed USA-166 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 1 February 2003, USA-166 was in an orbit with a perigee of , an apogee of , a period of 720.7 minutes, and 55 degrees of inclination to the equator.

The launch took place from Space Launch Complex 17A at the Cape Canaveral Air Force Station, and placed USA-168 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 3 April 2003, USA-168 was in an orbit with a perigee of , an apogee of , a period of 720.64 minutes, and 54.9 degrees of inclination to the equator. It is used to broadcast the PRN 21 signal, and operates in slot 3 of plane D of the GPS constellation.

The launch took place from Space Launch Complex 17A at the Cape Canaveral Air Force Station, and placed USA-175 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 22 February 2004, USA-175 was in an orbit with a perigee of , an apogee of , a period of 717.92 minutes, and 55.1 degrees of inclination to the equator. It is used to broadcast the PRN 22 signal, and operates in slot 2 of plane E of the GPS constellation.

The launch took place from Space Launch Complex 17A at the Cape Canaveral Air Force Station, and placed USA-190 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 25 November 2006, USA-190 was in an orbit with a perigee of , an apogee of , a period of 717.9 minutes, and 55 degrees of inclination to the equator. It is used to broadcast the PRN 31 signal, and operates in slot 2 of plane A of the GPS constellation.

The launch took place from Space Launch Complex 17A at the Cape Canaveral Air Force Station, and placed USA-192 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 17 January 2007, USA-192 was in an orbit with a perigee of , an apogee of , a period of 717.96 minutes, and 55 degrees of inclination to the equator. It is used to broadcast the PRN 12 signal, and operates in slot 4 of plane B of the GPS constellation.

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 23 December 1992, USA-85 was in an orbit with a perigee of , an apogee of , a period of 717.96 minutes, and 54.8 degrees of inclination to the equator. It was intended to broadcast signal PRN 32, but this was changed to PRN 01 on 28 January 1993 after it was discovered that receivers could not track the PRN 32 signal. The spacecraft was operated in slot 4 of plane F of the GPS constellation, and had a mass of .

The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 30 December 1990, USA-66 was in an orbit with a perigee of , an apogee of , a period of 717.98 minutes, and 54.9 degrees of inclination to the equator. It was initially given PRN 23, which it used until its retirement in February 2004; however, it was subsequently reactivated broadcasting PRN 32 and in February 2008 it rejoined the operational constellation. It is located in slot 5 of plane E of the GPS constellation.

Because of the increasing number of objects in space, NASA has adopted guidelines and assessment procedures to reduce the number of non-operational spacecraft and spent rocket upper stages orbiting the Earth. One method of postmission disposal is to allow reentry of these spacecraft, either from orbital decay (uncontrolled entry) or with a controlled entry. Orbital decay may be achieved by firing engines to lower the perigee altitude so that atmospheric drag will eventually cause the spacecraft to enter. However, the surviving debris impact footprint cannot be guaranteed to avoid inhabited landmasses.

The intensity of moonlight varies greatly depending on the lunar phase, but even the full Moon typically provides only about 0.05–0.1 lux illumination. When a full Moon around perigee (a "supermoon") is viewed around upper culmination from the tropics, the illuminance can reach up to 0.32 lux. From Earth, the apparent magnitude of the full Moon is only about that of the Sun. The color of moonlight, particularly around full moon, appears bluish to the human eye compared to most artificial light sources due to the Purkinje effect.

For orbital periods longer than the Earth's rotational period, an increase in orbital period corresponds to a longitudinal stretching out of the (apparent retrograde) ground track. A satellite whose orbital period is equal to the rotational period of the Earth is said to be in a geosynchronous orbit. Its ground track will have a "figure eight" shape over a fixed location on the Earth, crossing the equator twice each day. It will track eastward when it is on the part of its orbit closest to perigee, and westward when it is closest to apogee.

It was then established that the craft's solar panels had deployed, giving engineers more time to restore control. It was soon discovered the spacecraft was adjusting its orbit, changing its expected re-entry from late November or December to as late as early 2012.David Warmflash, M.D. – Phobos-Grunt's Mysterious Thruster Activation: A Function of Safe Mode or Just Good Luck? (16 November 2011) – Universe Today Even though it had not been contacted, the spacecraft seemed to be actively adjusting its perigee (the point it is closest to Earth in its orbit).

This was the final launch of a satellite as part of the Dnepropetrovsk Sputnik programme. The first DS launch, DS-1 No.1, occurred in 1961, and the first successful launch was that of Kosmos 1 in 1962. Kosmos 1375 was placed into a low Earth orbit with a perigee of , an apogee of , 65.8 degrees of inclination, and an orbital period of 105 minutes. On 18 June 1982, it was successfully intercepted and destroyed by Kosmos 1379 in the final Soviet anti-satellite weapons test to be conducted.

Progress M1-5 carried of fuel with which to perform the manoeuvres to deorbit Mir. These were completed on 23 March, when three deorbit burns were made; the first two using just docking and attitude control thrusters, and the third using the main engine as well as the thrusters. The first burn began at 00:32:28 GMT, and lasted 21.5 minutes, leaving Mir in an orbit with a perigee of and an apogee of . The second burn, which began at 02:24 GMT and lasted 24 minutes, placed Mir into a by orbit.

The first major claim of another moon of Earth was made by French astronomer Frédéric Petit, director of the Toulouse Observatory, who in 1846 announced that he had discovered a second moon in an elliptical orbit around Earth. It was claimed to have also been reported by Lebon and Dassier at Toulouse, and by Larivière at Artenac Observatory, during the early evening of March 21, 1846. Petit proposed that this second moon had an elliptical orbit, a period of 2 hours 44 minutes, with apogee and perigee. This claim was soon dismissed by his peers.

Negotiations were slow to start in spite of the alternative $10M purchase proposal from the US Government which was 33% lower than the improved offer from the European/Asian investment group. The first signs of an orbital adjustment maneuver became evident one day after SES announced it was in sales negotiations on 24 April 2008, when the satellite's perigee rose by about to along with a slight rise in apogee to 35572 km. Also, for comparison, at the time Inclination was 48.989, Eccentricity was 0.708, and it had an orbital time of 638.12 min.

The crew completed eight successful test firing maneuvers of the service module's propulsion engine. They also tested the performance of all spacecraft systems and broadcast the first live televised coverage of crew activities. Apollo 7 was placed in an Earth-orbit with an apogee of and perigee of . The 260-hour, 4.5 million mile (7.25 Gm; 7.25 million km) shakedown flight was successfully concluded on October 22, 1968, with splashdown occurring in the Atlantic, 8 miles (15 km) from the carrier USS Essex and only from the predicted target.

TESS uses a novel highly elliptical orbit around the Earth with an apogee approximately at the distance of the Moon and a perigee of 108,000 km. TESS orbits Earth twice during the time the Moon orbits once, a 2:1 resonance with the Moon. The orbit is expected to remain stable for a minimum of ten years. Led by the Massachusetts Institute of Technology with seed funding from Google, on April 5, 2013, it was announced that TESS, along with the Neutron Star Interior Composition Explorer (NICER), had been selected by NASA for launch.

A second instrument, Doppler Orbit and Radio Positioning Integration by Satellite, or DORIS, is used to calculate precisely the spacecraft's orbit. An array of retroreflectors are also carried aboard the spacecraft, and allow measurements to be made from the ground to verify the orbital data provided by DORIS. Following launch, CryoSat-2 was placed into a low Earth orbit with a perigee of , an apogee of , 92 degrees of inclination and an orbital period of 99.2 minutes. It had a mass at launch of , and is expected to operate for at least three years.

This inertial direction is set to be in the velocity vector at apogee but with an out-of-plane component. The out-of-plane component removes the initial inclination set by the initial transfer orbit, while the in-plane component raises simultaneously the perigee and lowers the apogee of the intermediate geostationary transfer orbit. In case of using the Hohmann transfer orbit, only a few days are required to reach the geosynchronous orbit. By using low-thrust engines or electrical propulsion, months are required until the satellite reaches its final orbit.

Mission profile As the first crewed spacecraft to orbit more than one celestial body, Apollo8's profile had two different sets of orbital parameters, separated by a translunar injection maneuver. Apollo lunar missions would begin with a nominal circular Earth parking orbit. Apollo8 was launched into an initial orbit with an apogee of and a perigee of , with an inclination of 32.51° to the Equator, and an orbital period of 88.19 minutes. Propellant venting increased the apogee by over the 2hours, 44 minutes, and 30 seconds spent in the parking orbit.

The spacecraft entered an orbit with a perigee of 200 km and an apogee of 380,000 km, and separated from the carrier rocket as planned. It was the first time that a Chinese lunar probe directly entered an Earth-to-Moon transfer orbit without orbiting the Earth first. After the launch, Chang'e 2 arrived in its lunar orbit within 4 days and 16 hours. Later, the probe lowered its orbit to , with a perilune of . Chang'e 2 entered its 100 km working orbit on 9 October 2010 after three successful brakings.

The discovery of the Van Allen radiation belt by the Explorer satellites was considered to be one of the outstanding discoveries of the IGY. Explorer 3 was placed in an orbit with a perigee of 186 kilometers and an apogee of 2799 kilometers having a period of 115.7 minutes. Its total weight was 14.1 kilograms, of which 8.4 kg was instrumentation. The instrument section at the front end of the satellite and the empty scaled-down fourth-stage rocket casing orbited as a single unit, spinning around its long axis at 750 revolutions per minute.

Vostok-2, s/n T15000-07, was used to launch Kosmos 7. The launch was conducted from Site 1/5 at the Baikonur Cosmodrome, and occurred at 09:18:31 GMT on 28 July 1962. Kosmos 7 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 64.95°, and an orbital period of 90.1 minutes. It conducted a four-day mission, before being deorbited and landing by parachute on 1 August 1962, and recovered by the Soviet forces in the steppe in Kazakhstan.

It was launched on a Vostok-K rocket, which was making its seventh flight. It was the last Zenit launch to use the Vostok-K, before launches switched to the Vostok-2 starting with the next launch attempt in June 1962. The launch was conducted from Site 1/5 at the Baikonur Cosmodrome, and occurred at 10:02:00 GMT on 26 April 1962. Kosmos 4 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 65.0°, and an orbital period of 90.6 minutes.

To maximize the number of sources occulted by the Moon, a highly eccentric orbit (e ~ 0.93) with a 90.6 hr period and an inclination of 73° was chosen. The initial apogee was 191,000 km and perigee 350 km. To be outside the Earth's radiation belts, the scientific instruments were operated above ~50,000 km, giving up to ~76 hr per 90 hr orbit. There was no need for any onboard data storage as Exosat was visible from the ground station at Villafranca, Spain for practically the entire time the scientific instruments were operated.

It was launched on Kosmos-2I 63S1 s/n 6LK. It was the third flight of the Kosmos-2I, and the first to successfully reach orbit. It was also the first Kosmos rocket of any type to successfully place a satellite into orbit. The launch was conducted from Mayak-2 at Kapustin Yar, and occurred at 11:59:00 GMT on 16 March 1962. Kosmos 1 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 49.0°, and an orbital period of 93.1 minutes.

The Agena Target Vehicle as seen from Gemini 8 during rendezvous. Their first course adjustment was made at one hour and 34 minutes into the mission, when the astronauts lowered their apogee slightly with a five-second Orbit Attitude and Maneuvering System (OAMS) thruster burn. The second adjustment was made near apogee of the second orbit, and raised both the apogee and perigee by adding to their speed. The third adjustment was made over the Pacific Ocean, a southward orbital plane change, made with a sideways thruster burn.

Young was also backup commander of Apollo 13 and Apollo 17 and Cernan was backup commander of Apollo 14. The Apollo 10 crew are also the humans who have traveled the farthest away from home, some from their homes and families in Houston. While most Apollo missions orbited the Moon at the same from the lunar surface, the distance between the Earth and Moon varies by about , between perigee and apogee, throughout each lunar month, and the Earth's rotation makes the distance to Houston vary by another each day.

The spacecraft was operated at a longitude of 15° west, over the Atlantic Ocean. It was briefly relocated to 35° west in 1972, but had returned to 15° west by the following year. It acquired the unofficial nickname Canary Bird because of the association of the mission with Maspalomas Station, the ground station which is located in the Canary Islands. As of February 7, 2014 the derelict Intelsat II F-3 was in an orbit with a perigee of , an apogee of , inclination of 5.81 degrees and an orbital period of 23.94 hours.

This orbital precession is also called apsidal precession and is the rotation of the Moon's orbit within the orbital plane, i.e. the axes of the ellipse change direction. The Moon's major axis – the longest diameter of the orbit, joining its nearest and farthest points, the perigee and apogee, respectively – makes one complete revolution every 8.85 Earth years, or 3,232.6054 days, as it rotates slowly in the same direction as the Moon itself (direct motion). The Moon's apsidal precession is distinct from the nodal precession of its orbital plane and axial precession of moon itself.

As a result, the angular velocity of the Moon varies as it orbits Earth and hence is not always equal to the Moon's rotational velocity. When the Moon is at its perigee, its orbital motion is faster than its rotation, and this allows us to see up to eight degrees of longitude of its eastern (right) far side. Conversely, when the Moon reaches its apogee, its orbital motion is slower than its rotation, revealing eight degrees of longitude of its western (left) far side. This is referred to as longitudinal libration.

The satellite was officially launched the 12th of February 2005 at 21:03 UT on board an Ariane-5 ECA rocket from the Guyana Space Center. Its orbit is geostationary (GEO) 29º East, around 35,800 km high (35,782.6 km of perigee and 35,803.7 km of apogee) with 0º of inclination, a period of 1,436.1 minutes and a semi-major axis of 42,164 km. During its operation life, the XTAR-EUR is being monitored from Arganda del Rey and Maspalomas Station. While the operating companies are based on Washington, D.C., Madrid and Palo Alto.

The king tides occur when the Earth, Moon and Sun are aligned at perigee and perihelion, resulting in the largest tidal range seen over the course of a year. So, tides are enhanced when the Earth is closest to the Sun around January 2 of each year. They are reduced when it is furthest from the Sun, around July 2.Tidal Variations — The Influence of Position and Distance NOAA ocean service education The predicted heights of a king tide can be further augmented by local weather patterns and ocean conditions.

The launch vehicle will have a target, and the guidance system will alter the steering commands to attempt to get to the final end state. At least one variable (apogee, perigee, inclination, etc) must be left free to alter the values of the others, otherwise the dynamics would be overconstrained. An instantaneous launch window allows the RAAN be the uncontrolled variable. While some spacecraft such as the Centaur upper stage can steer and adjust its RAAN after launch, choosing an instantaneous launch window allows the RAAN to be pre-determined for the spacecraft's guidance system.

The launch took place from Space Launch Complex 17A at the Cape Canaveral Air Force Station, and placed USA-201 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 18 May 2008, USA-201 was in an orbit with a perigee of , an apogee of , a period of 717.98 minutes, and 55.1 degrees of inclination to the equator. It is used to broadcast the PRN 07 signal, and operates in slot 4 of plane A of the GPS constellation.

1965, The launch was normal and the payload was inserted into orbit approximately 10.6 minutes after lift-off. The total mass placed in orbit, including the spacecraft, Pegasus B, adapter, instrument unit, and S-IV stage, was 34,113 pounds (15,473 kg). The perigee and apogee were 314.0 and 464.1 miles (505 and 747 km), respectively; the orbital inclination was 31.78'. The 1397 kilogram (3080-pound) Pegasus 2 satellite was also carried to orbit by SA-8, being stowed inside the boilerplate's service module, and remaining attached to the S-IV stage.

The launch of Ariel 2 The launch of Ariel 2 was conducted by the United States National Aeronautics and Space Administration, using a Scout X-3 rocket. The launch occurred at 17:25:23 GMT on 27 March 1964, from Launch Area 3 at the Wallops Flight Facility. Ariel 2 was placed into a low Earth orbit, with a perigee of , an apogee of , 51.6 degrees of inclination and an orbital period of 101.2 minutes as of 3 May 1964. It ceased operations in November 1964, and subsequently decayed from orbit on 18 November 1967.

Due to the small size of the dish, only very strong radio sources could be observed with SVLBI arrays incorporating it. Another SVLBI satellite, a 10-meter radio telescope Spektr-R, was launched in July 2011 and made observations until January 2019. It was placed into a highly elliptical orbit, ranging from a perigee of 10,652 km to an apogee of 338,541 km, making RadioAstron, the SVLBI program incorporating the satellite and ground arrays, the biggest radio interferometer to date. The resolution of the system reached 8 microarcseconds.

Comet C/2013 UQ4 (Catalina), images from July 9th, 10th and 11th 2014, showing the evolution of the shape of the comet with its relative position to Earth (i.e. perigee was on July 10th, at a distance of 47 million kilometres (29 million miles). C/2013 UQ4 (Catalina) is a Solar System comet that came close to the Earth on July 10, 2014, at a distance of .Comet C/2013 UQ4 Catalina at minimum distance from the Earth: an image (10 July 2014), Gianluca Masi, The Virtual Telescope Project, 10 July 2014.

Launch of H-IIA F13 carrying SELENE (Photo by Narita Masahiro) SELENE launched on September 14, 2007 at 01:31:01 UTC on an H-IIA (Model H2A2022) carrier rocket from Tanegashima Space Center into a (perigee) / (apogee) geocentric parking orbit. The total launch mass was . The SELENE mission was originally scheduled to launch in 2003, but rocket failures on another mission and technical difficulties delayed the launch until 2007. Launch was planned for August 16, 2007, but was postponed when some electronic components were found to be installed incorrectly.

The Vostok-2, s/n T15000-03, was used to launch Kosmos 10. The launch was conducted from Site 1/5 at the Baikonur Cosmodrome, and occurred at 09:21 GMT on 21 October 1962. Kosmos 10 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 65.0°, and an orbital period of 90.2 minutes. It conducted a four-day mission, before being deorbited and landing by parachute on 21 October 1962, and recovered by the Soviet forces in the steppe in Kazakhstan.

The Vostok-2, s/n T15000-06, was used to launch Kosmos 9. The launch was conducted from Site 1/5 at the Baikonur Cosmodrome, and occurred at 09:39:51 GMT on 27 September 1962. Kosmos 9 was placed into a low Earth orbit with a perigee of , an apogee of , an inclination of 65.0°, and an orbital period of 90.9 minutes. It conducted a four-day mission, before being deorbited and landing by parachute on 1 October 1962, and recovered by the Soviet forces in the steppe in Kazakhstan.

A Delta N, also known as the Thor-Delta N, was used to place it into orbit. The launch occurred at 01:55:08 UTC, from Space Launch Complex 2E at Vandenberg Air Force Base. The launch of TD-1A marked the final flight of the Delta N, and the last launch from Space Launch Complex 2E. TD-1A was placed into a low Earth orbit; on 11 April 1974 it was tracked in an orbit with a perigee of , an apogee of , 97.5 degrees of inclination, and a period of 95.32 minutes.

Once the cosmonauts had unloaded the cargo delivered by Progress 1, they loaded refuse onto the freighter for disposal. On 6 February 1978, Progress 1 was catalogued in a low Earth orbit with a perigee of and an apogee of , inclined at 51.66° and with a period of 91.3 minutes. Progress 1 undocked from Salyut 6 at 05:54 UTC on 6 February. It remained in orbit for two more days, finally being deorbited to a destructive reentry over the Pacific Ocean at around 02:45 UTC on 8 February 1978.

On 4 November, the day after it was deployed, Sputnik 40 was in a low Earth orbit with a perigee of , an apogee of , an inclination of 51.6 degrees, and a period of 92.13 minutes. The satellite was given the International Designator 1997-058C, and was catalogued by the United States Space Command as 24958. It ceased operations on 29 December 1997 when its batteries expired, and subsequently decayed from orbit on 21 May 1998. The backup satellite remained aboard Mir, and was destroyed when Mir was deorbited on 23 March 2001.

Scott is also the editor of the anthology Drivel: Deliciously Bad Writing by Your Favorite Authors (Perigee Books, 2014), cited as "classic" by Vanity Fair and featuring contributions by Dave Eggers, Gillian Flynn, Mary Roach, Rick Moody and Chuck Palahniuk, among others. She is the subject of "Julia", an episode in the Heavyweight podcast series by Jonathan Goldstein, named "One of the 10 Best Podcast Episodes of 2016" by Elle magazine. A native of Montreal, Scott maintains dual Canadian and American citizenship. She currently resides in Oakland, California.

Arase, formerly known as Exploration of energization and Radiation in Geospace (ERG), is a scientific satellite to study the Van Allen belts. It was developed by the Institute of Space and Astronautical Science of JAXA. While there was a scientist working on a similar project with the surname Arase, the satellite's name has nothing to do with him but instead named after a river beside the launch point. It was launched aboard Epsilon launch vehicle at 11:00:00, 20 December 2016 UTC into apogee height 32250 km, perigee 214 km orbit.

Iris was mainly intended to study X-ray and particle emissions from the Sun, however, it is credited with some extra-solar observations. ESRO 2B (Iris) was the first successful ESRO satellite launch. Iris was launched on May 17, 1968, had an elliptical orbit with (initially) apogee 1086 km, perigee 326 km, and inclination 97.2°, with an orbital period of 98.9 minutes. The satellite carried seven instruments to detect high energy cosmic rays, determine the total flux of solar X-rays, and measure trapped radiation, Van Allen belt protons and cosmic ray protons.

This limited maneuvering capability is still quite useful. By varying the magnetic sail's field strength over the course of its orbit, a magnetic sail can give itself a "perigee kick" raising the altitude of its orbit's apogee. Repeating this process with each orbit can drive the magnetic sail's apogee higher and higher, until the magnetic sail is able to leave the planetary magnetosphere and catch the solar wind. The same process in reverse can be used to lower or circularize the apogee of a magsail's orbit when it arrives at a destination planet.

Courier 1B launched on 4 October 1960 at 17:45:00 GMT from the Atlantic Missile Range at Cape Canaveral, Florida. The launch vehicle was a Thor-Able-Star, comprising a modified USAF Thor IRBM first stage and a USAF Able-Star upper stage with a re-startable liquid engine. The satellite was successfully inserted into an orbit with a perigee of , an apogee of , an inclination of 28.33°, and an Orbital period of 106.8 minutes. Messages were successfully received and transmitted and the satellite operated nominally until a command system failure ended communications 17 days after launch.

Approach to the ISS HTV-1 before capture HTV-1 was successfully launched at 17:01:46 UTC on 10 September 2009, to the initial orbit of of perigee, a apogee of , an inclination of 51.69° (planned ± / ± / 51.67° ± 0.15°). The launch took place from the (Yoshinobu Launch Complex (Yoshinobu-2) at the Tanegashima Space Center, and was the first to use the second pad of the complex. Flight operations are chronicled using Flight Day (FD), the ISS crew timeline. Arrival of HTV-1 occurred during Expedition 20, (Gennady Padalka, Commander, Michael Barratt, Nicole Stott, Frank De Winne, Roman Romanenko, and Robert Thirsk).

Two out of three Progress M1-5 propulsion firings, at approximately 90 minute intervals, were used to bring the perigee of Mir down to an altitude of above the Earth's surface. A tough contact with the atmosphere occurred at altitude, when some of the external light elements of Mir were torn off due to the rush through the rarefied air. At an altitude of sufficient heating from Mir hull created a glowing halo of hot plasma. At about that time, the orbital complex broke apart and several of Mirs elements, surrounded by the plasma, were visible from Fiji against the evening sky.

Kosmos 115 was operated in a low Earth orbit, at an epoch of 22 April 1966, it had a perigee of , an apogee of , an inclination of 65.0° and an orbital period of 89.3 minutes. After eight days in orbit, Kosmos 115 was deorbited, with its return capsule descending under parachute and landing at 09:07 GMT on 28 April 1966 and the capsule was recovered by Soviet force. There was abnormal operation of a SA-10 camera. Due to a camera malfunction, the satellite failed to take all of the images it had been programmed to produce.

This was the first time a Voskhod had been used to launch a Zenit-2 satellite; previous launches had used Vostok-2 rockets while the Voskhod was typically used to launch Zenit-4 spacecraft. Kosmos 120 was operated in a low Earth orbit, at an epoch of 8 June 1966, it had a perigee of , an apogee of , an inclination of 51.8° and an orbital period of 89.4 minutes. After eight days in orbit, Kosmos 120 was deorbited, with its return capsule descending under parachute, landing at 09:36 GMT on 16 June 1966, and recovered by Soviet force.

This coverage gap was much smaller than originally feared, thanks to USA-224's earlier-than-planned launch and operational changes to extend the lifetime of USA-161. As the fifteenth KH-11 satellite to be launched, USA-224 is a member of one of the later block configurations occasionally identified as being a separate system. Details of its mission and orbit are classified, but amateur observers have tracked it in low Earth orbit. Shortly after launch it was in an orbit with a perigee of , an apogee of and 97.9 degrees of inclination, typical for an operational KH-11 satellite.

The supermoon of March 19, 2011 (right), compared to an average full moon of January 18, 2011 (left), as viewed from Earth A full moon at perigee appears roughly 14% larger in diameter than at apogee. Many observers insist that the moon looks bigger to them. This is likely due to observations shortly after sunset when the moon is near the horizon and the moon illusion is at its most apparent. While the moon's surface luminance remains the same, because it is closer to the earth the illuminance is about 30% brighter than at its farthest point, or apogee.

An annular solar eclipse occurred at the moon's descending node of the orbit on May 10, 1994. It was visible over a wide swath of North America, from Baja California across the Midwest of the United States up through Ontario and Nova Scotia in Canada. Occurring only 1.6 days after apogee (Perigee on May 9, 1994 at 02:18 UTC or May 8, 1994 at 22:18 EDT or 19:18 PDT), the moon's apparent diameter was smaller. This solar eclipse belonged to Saros series 128 because occurred at the Moon's descending node and 128 is an even number.

The Ranger 1 and 2 Block I missions were virtually identical. Spacecraft experiments included a Lyman-alpha telescope, a rubidium-vapor magnetometer, electrostatic analyzers, medium-energy-range particle detectors, two triple coincidence telescopes, a cosmic-ray integrating ionization chamber, cosmic dust detectors, and scintillation counters. The goal was to place these Block I spacecraft in a very high Earth orbit with an apogee of and a perigee of . From that vantage point, scientists could make direct measurements of the magnetosphere over a period of many months while engineers perfected new methods to routinely track and communicate with spacecraft over such large distances.

This mission was intended to orbit the Moon and was configured identically to the future Luna 10 mission (1966-027A). It was launched on 1 March 1966 at 11:03:49 GMT via Molniya 8K78M s/n U15000-50 rocket from Site 31/6 into Earth parking orbit, but the Blok-L upper stage lost roll control and failed to fire the spacecraft into a lunar trajectory. It had a perigee of , an apogee of , an inclination of 51.9°, and an orbital period of 88.6 minutes. It was designated Kosmos 111 and reentered two days after launch, on 3 March 1966.

The manoeuvre lasted 228.7 seconds, and left the space station in an orbit with a perigee of and an apogee of . Progress M-08M was launched on 27 October 2010, and successfully docked two days later. The third manoeuvre was conducted on 22 December 2010, when eight thrusters were again used to raise the space station's orbit. This manoeuvre raised the orbit of the space station by to in preparation for the arrival of the Progress M-09M spacecraft, which is scheduled to launch on 28 January 2011, and for the docking of OV-103 on the STS-133 mission.

The launch took place from Space Launch Complex 17A at the Cape Canaveral Air Force Station, and placed USA-150 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 11 June 2000, USA-150 was in an orbit with a perigee of , an apogee of , a period of 718.02 minutes, and 54.9 degrees of inclination to the equator. It is used to broadcast the PRN 20 signal, and operates in slot 1 of plane E of the GPS constellation, having replaced USA-35, the first operational GPS satellite.

The launch took place from Space Launch Complex 17A at the Cape Canaveral Air Force Station, and placed USA-151 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37FM apogee motor. By 27 July 2000, USA-151 was in an orbit with a perigee of , an apogee of , a period of 722.98 minutes, and 55 degrees of inclination to the equator. It is used to broadcast the PRN 28 signal, and operates in slot 3 of plane B of the GPS constellation, having originally been operated in slot 5.

Animation of Herschel Space Observatory trajectory from 14 May 2009 to 31 August 2013 The spacecraft, built in the Cannes Mandelieu Space Center, under Thales Alenia Space Contractorship, was successfully launched from the Guiana Space Centre in French Guiana at 13:12:02 UTC on 14 May 2009, aboard an Ariane 5 rocket, along with the Planck spacecraft, and placed on a very elliptical orbit on its way towards the second Lagrangian point.Herschel Latest News, on line herschel.esac.esa.int The orbit's perigee was 270.0 km (intended ), apogee 1,197,080 km (intended ), inclination 5.99 deg (intended ).Herschel Science Centre Operations (B)Log.

Using the nominal orbit, the asteroid was expected to have an apparent magnitude of about 16 and pass from Earth. Closest approach (perigee-geocentrical) was around 00:15 UTC on 18 February plus or minus about 13 hours. Even with an observation arc of 9 days, it was known that the minimum possible close approach distance to Earth on 18 February 2014 was with a small chance that the asteroid would pass as far as from Earth. Due to the uncertainty region of the asteroid, the asteroid could have been 75 degrees from the nominal position in the sky on 18 February 2014.

The musical opened on Broadway on April 15, 1971, at the Broadhurst Theatre, where it ran for 35 performances and nine previews. The cast included Mildred Natwick, Lillian Roth, Hans Conried, and Lillian Hayman. Natwick was nominated for the Tony Award for Best Actress in a Musical. Veteran Broadway actor David Burns was also a member of the cast, until he collapsed onstage from a heart attack during a preview performance at Philadelphia's Forrest Theatre and died soon after;Alan W. Petrucelli, "Morbid Curiosity: The Disturbing Demises of the Famous and Infamous", Perigee Trade (2009), p 114.

A Molniya orbit (, "Lightning") is a type of satellite orbit designed to provide communications and remote sensing coverage over high latitudes. It is a highly elliptical orbit with an inclination of 63.4 degrees, an argument of perigee of 270 degrees, and an orbital period of approximately half a sidereal day. The name comes from the Molniya satellites, a series of Soviet/Russian civilian and military communications satellites which have used this type of orbit since the mid-1960s. The Molniya orbit has a long dwell time over the hemisphere of interest, while moving very quickly over the other.

During the ascent the rocket performed a dog-leg manoeuvre to increase its inclination sufficiently to attain sun-synchronous orbit. The satellite was deployed into a sun-synchronous polar orbit with an apogee of , a perigee of , 97.4 degrees of orbital inclination, and an orbital period of 95 minutes and 29 seconds. The spacecraft separated from the rocket's third stage at 00:59:13; nine minutes and 27 seconds after liftoff. The U.S. Space Command began to track three objects from the launch, giving Kwangmyŏngsŏng-3 the Satellite Catalog Number 39026 and the international designator 2012-072A.

Intelsat 603 was launched at 11:52:31 UTC on 14 March 1990, atop a Commercial Titan III carrier rocket, flight number CT-2, with an Orbus-21S upper stage. The launch took place from Launch Complex 40 at the Cape Canaveral Air Force Station, and was intended to place Intelsat 603 into a geosynchronous transfer orbit. The Orbus-21S failed to separate from the Titan's second stage, and as a result it was unable to fire, leaving Intelsat 603 in low Earth orbit. Following the launch failure, Intelsat commissioned NASA to launch a replacement perigee motor to raise the satellite's orbit.

Aesthetic inquiry on everyday life owes much of its approach to John Dewey’s (1934) pragmatist aesthetics, even if he was interested in grounding mainly artistic experience. Dewey pointed at a variety of circumstances in which sensibility is present emphasizing the importance of feeling, energy, and rhythm in every creature's intercourse with its environment. He thus stressed not only the artistic but the everyday doings and undergoings that involve alertness and intensity of experience.Dewey, John Art as Experience (New York: Perigee,1934) Dewey explored aesthetics from the subjects' experience rather than from objects' status as artworks and museum collections.

In fact, the Lunar Mechanism which is part of the Antikythera Mechanism depicts the motion of the Moon and its phase, for a given time, using a train of four gears with a pin and slot device which gives a variable lunar velocity that is very close to the second law of Kepler, i.e. it takes into account the fast motion of the Moon at perigee and slower motion at apogee. This discovery proves that Hipparchus mathematics were much more advanced than Ptolemy describes in his books, as it is evident that he developed a good approximation of Kepler΄s second law.

Perigee Books. . P. 526. At 22 in 1904, Hall was in the first stage production of Mrs. Wiggs of the Cabbage Patch. His Broadway credits include The Only Girl (1914), Have a Heart (1917), Civilian Clothes (1919), The French Doll (1922), Still Waters (1926), Buy, Buy, Baby (1926), Mixed Doubles (1927), Behold the Bridegroom (1927), The Common Sin (1928), Sign of the Leopard (1928), Security (1929), Fifty Million Frenchmen (1929), Everything's Jake (1930), Philip Goes Forth (1931), Chrysalis (1932), Thoroughbred (1933), Re- echo (1934), They Shall Not Die (1934), Spring Freshet (1934), All Rights Reserved (1934), and Rain from Heaven (1934).

Sea Launch launches from a floating platform directly on the equator in the Pacific Ocean. Expendable launchers generally reach GTO directly, but a spacecraft already in a low Earth orbit (LEO) can enter GTO by firing a rocket along its orbital direction to increase its velocity. This was done when geostationary spacecraft were launched from the space Shuttle; a "perigee kick motor" attached to the spacecraft ignited after the shuttle had released it and withdrawn to a safe distance. Although some launchers can take their payloads all the way to geostationary orbit, most end their missions by releasing their payloads into GTO.

Luna 9 was launched by a Molniya-M rocket, serial number 103-32, flying from Site 31/6 at the Baikonur Cosmodrome in the Kazakh Soviet Socialist Republic. Liftoff took place at 11:41:37 GMT on 31 January 1966. The first three stages of the four-stage carrier rocket injected the payload and fourth stage into low Earth orbit, at an altitude of and an inclination of 51.8°. The fourth stage, a Blok-L, then fired to raise the perigee of the orbit to a new apogee approximately , before deploying Luna 9 into a highly elliptical geocentric orbit.

Its duration is about 27.21222 days on average. A synodic month is longer than a sidereal month because the Earth-Moon system is orbiting the Sun in the same direction as the Moon is orbiting the Earth. The Sun moves eastward with respect to the stars (as does the Moon) and it takes about 2.2 days longer for the Moon to return to the same apparent position with respect to the Sun. An anomalistic month is longer than a sidereal month because the perigee moves in the same direction as the Moon is orbiting the Earth, one revolution in nine years.

Originally intended for a lunar orbit, mission controllers worried that the spacecraft's trajectory was too fast to guarantee lunar capture. Consequently, mission managers opted for a backup plan of placing the craft into an eccentric Earth orbit with a perigee of 265,679 km and an apogee of 480,762 km -- still reaching distances beyond the Moon's orbit. Despite not attaining the intended lunar orbit, the mission met many of its original goals in exploring solar wind, interplanetary plasma, and solar X-rays. Principal investigator James Van Allen used electron and proton detectors aboard the spacecraft to investigate charged particle and X-ray activity.

The whole balloon package weighed two pounds. Divided into five sections of different colors - uncolored aluminum, yellow, orange, white, and a phosphorescent coating that appeared white by day and blue by night - the balloon was to be cast off near perigee after the first orbital pass to float freely at the end of a 100-foot nylon line. The purposes of the balloon experiment were to study the effects of space on the reflection properties of colored surfaces through visual observation and photographic studies and to obtain aerodynamic drag measurements by use of a strain gauge.

Upon successfully reaching orbit, it was assigned the Harvard designation 1961 Omega 1. Discoverer 30 was operated in a low Earth orbit, with a perigee of , an apogee of , 82.6 degrees of inclination, and a period of 91.7 minutes. The satellite had a mass of , and was equipped with a panoramic camera with a focal length of , which had a maximum resolution of . Images were recorded onto film, and returned in a Satellite Recovery Vehicle two days after launch; however, like the previous mission, all of the images returned were found to be out of focus.

A crescent Moon over Kingman, Arizona Each of the four intermediate phases lasts approximately seven days (7.38 days on average), but varies slightly due to lunar apogee and perigee. The number of days counted from the time of the new moon is the Moon's "age". Each complete cycle of phases is called a "lunation". The approximate age of the Moon, and hence the approximate phase, can be calculated for any date by calculating the number of days since a known new moon (such as January 1, 1900 or August 11, 1999) and reducing this modulo 29.530588853 (the length of a synodic month).

This image of the Earth and Moon was the first picture taken by the Nozomi camera. Animation of Nozomi's orbit around Sun It flew by Earth on December 20, 1998, at a perigee of about 1000 km. The gravitational assist from the flyby coupled with a 7 minute burn of the bipropellant rocket put Nozomi into an escape trajectory towards Mars. It was scheduled to arrive at Mars on October 11, 1999, at 7:45:14 UT, but a malfunctioning valve during the Earth swingby resulted in a loss of fuel and left the spacecraft with insufficient acceleration to reach its planned trajectory.

The Weather Bureau described the storm as "one of the most damaging extratropical cyclones to hit the United States coastline," with damage estimated around $200 million. The storm destroyed 1,793 houses, and damaged another 16,782. According to the American Red Cross, the storm killed 40 people in the United States, with 1,252 people injured. At the same time of the storm reaching its maturity, the moon was at its perigee - its closest point to Earth during its 28-day elliptical orbit - while the moon was also in alignment with the sun and moon, a set of conditions known as the Perigean spring tide.

The Zenit-3F, also known as the Zenit-2SB/Fregat, is a 3-stage derivative of the Zenit-2M, using a Fregat upper stage, as already used on the Soyuz, to propel spacecraft to higher orbits. It made its maiden flight in January 2011, with the Elektro-L No.1 spacecraft for the Russian government. Later the same year, another launch carried Spektr-R, a space telescope, into an orbit with a perigee of and an apogee of . The most recent launch occurred on 26 December 2017 from Baikonur Cosmodrome when the rocket lifted off with the Angolian Angosat 1 spacecraft.

A space tower is a tower that would reach outer space. To avoid an immediate need for a vehicle launched at orbital velocity to raise its perigee, a tower would have to extend above the edge of space (above the 100 km Kármán line), but a far lower tower height could reduce atmospheric drag losses during ascent. If the tower went all the way to geosynchronous orbit at approximately , objects released at such height could then drift away with minimal power and would be in a circular orbit. The concept of a structure reaching to geosynchronous orbit was first conceived by Konstantin Tsiolkovsky.

The launch of Explorer 9 Explorer 9 was launched from Launch Area 3 at the Wallops Flight Center, atop a Scout X-1 rocket with the serial number ST-4. It was the first spacecraft launched from Wallops Island to achieve orbit, with one previous attempt having failed. The launch occurred at 13:05:00 UTC on 16 February 1961, and resulted in Explorer 9 being deployed into an orbit with an apogee of , a perigee of , 38.8 degrees of inclination and a period of 118.4 minutes. It was assigned the Harvard designation 1961 Delta 1.

Hinode (; , , Sunrise), formerly Solar-B, is a Japan Aerospace Exploration Agency Solar mission with United States and United Kingdom collaboration. It is the follow-up to the Yohkoh (Solar-A) mission and it was launched on the final flight of the M-V rocket from Uchinoura Space Center, Japan on 22 September 2006 at 21:36 UTC (23 September, 06:36 JST). Initial orbit was perigee height 280 km, apogee height 686 km, inclination 98.3 degrees. Then the satellite maneuvered to the quasi-circular sun-synchronous orbit over the day/night terminator, which allows near-continuous observation of the Sun.

A mass driver would accelerate a payload up to some high speed which would not be enough for orbit. It would then release the payload, which would complete the launch with rockets. This would drastically reduce the amount of velocity needed to be provided by rockets to reach orbit. Well under a tenth of orbital velocity from a small rocket thruster is enough to raise perigee if a design prioritizes minimizing such, but hybrid proposals optionally reduce requirements for the mass driver itself by having a greater portion of delta-v by a rocket burn (or orbital momentum exchange tether).

It was designed and manufactured by [Lockheed Martin], and launched at 11:23:59.997 UTC on February 24, 1996 aboard a McDonnell Douglas Delta II 7925-10 rocket from launch pad 2W at Vandenberg Air Force Base in Lompoc, California, to study the polar magnetosphere. The spacecraft was placed into a highly elliptical orbit with apogee at 9 Earth radii and perigee at 1.8 Earth radii (geocentric), 86 degrees inclination, with a period of around 18 hours. The apogee was initially over the northern polar region, but has since been precessing south at about 16° per year.

A total solar eclipse occurred at the Moon's descending node of the orbit on July 22, 2009 with a magnitude of 1.0799. It was the longest total solar eclipse during the 21st century, the longest total solar eclipse during the 3rd millennium will be on 16 July 2186. It lasted a maximum of 6 minutes and 38.86 seconds off the coast of Southeast Asia, causing tourist interest in eastern China, Pakistan, Japan, India, Nepal and Bangladesh. Its greatest magnitude was 1.07991, occurring only 6 hours, 18 minutes after perigee, with greatest eclipse totality lasting 6 minutes, 38.86 seconds during the Total Solar Eclipse of July 22, 2009.

Returning spacecraft (including all potentially manned craft) have to find a way of slowing down as much as possible while still in higher atmospheric layers and avoid hitting the ground (lithobraking) or burning up. For many orbital space flights, initial deceleration is provided by the retrofiring of the craft's rocket engines, perturbing the orbit (by lowering perigee down into the atmosphere) onto a suborbital trajectory. Many spacecraft in low-Earth orbit (e.g., nanosatellites or spacecraft that have run out of station keeping fuel or are otherwise non-functional) solve the problem of deceleration from orbital speeds through using atmospheric drag (aerobraking) to provide initial deceleration.

Originally planned for launch in March 1964, electrical issues with the Scout X-4 booster's harness and subsequent pad requirements resulted in five months of delay. On August 25, 1964, at 13:43 UT, Explorer 20 was launched into a near-perfect orbit, with an apogee of and a perigee of , an inclination to the equator of 80°, and a period of 104 minutes. Upon reaching orbit, the antennas extended from the spacecraft, and tests of the primary and secondary experiments were completed within the first orbit. The satellite was spin stabilized at 1.53 rpm just after antenna extension, with the spin axis initially very close to the orbit plane.

The launch took place at 12:00:01 GMT on 19 December 1966, and following its successful arrival in orbit the spacecraft received its Kosmos designation; along with the International Designator 1966-115A and the Satellite Catalog Number 02624. Kosmos 136 was operated in a low Earth orbit, at an epoch of 19 December 1966, it had a perigee of , an apogee of , an inclination of 64.6°, and an orbital period of 89.4 minutes. After eight days in orbit, Kosmos 136 was deorbited, with its return capsule descending under parachute, landing at 06:00 GMT on 27 December 1966, and recovered by Soviet force.

Tian Hui-1 (also known as Mapping Satellite I) is a Chinese earth observation satellite built by Dong Feng Hong, a China Aerospace Science and Technology Corporation (CASC). Tian Hui-1 was launched on 6 May 2012 at 9:10 UTC on a Long March 2 2D booster rocket into a sun-synchronous, polar orbit with an apogee of and perigee of . According to the Chinese Ministry of Defense the new satellite carries scientific experiments and is to be used for the evaluation of ground resources and mapping. Tian Hui 1 is equipped with two different camera systems in the visible and infrared range.

The Atlas V's ascent was directed slightly south of east over the Atlantic Ocean. Following the rocket's first stage, additional burns in subsequent stages steered the spacecraft towards the altitude needed for geosynchronous orbit. Spacecraft separation from the launch vehicle occurred over Indonesia roughly 3.5 hours after launch, placing GOES-R in an elliptical low-inclination geostationary transfer orbit with a perigee of and an apogee of . The spacecraft then initiated several burns using its own independent propulsion systems to refine its orbit to place it in the intended geostationary position, with eight days dedicated to increasing its orbital radius and four to orbital fine-tuning.

Bob Furmanek and Ron Palumbo, Abbott and Costello in Hollywood, Perigee Books, 1991, p.211Biography by Bruce Eder at Allmusic.com. Accessed 24 May 2012 She was married to Phil Kahl, an associate of Roulette Records owner Morris Levy, and won a recording contract with the company, releasing a succession of pop and novelty records in the mid and late 1950s, including "Doodle Doodle Doo" (1957). In the same year, she featured in the early rock and roll movie, Mister Rock and Roll, which starred Alan Freed as himself and also featured Chuck Berry, Little Richard, Frankie Lymon, Lionel Hampton, Brook Benton and Ferlin Husky.

Comet Lulin (official designation C/2007 N3 (Lulin), Traditional Chinese:鹿林彗星) is a non-periodic comet. It was discovered by Ye Quanzhi and Lin Chi-Sheng from Lulin Observatory. It peaked in brightness and arrived at perigee for observers on Earth on February 24, 2009, at magnitude +5, and at from Earth. The comet was near conjunction with Saturn on February 23, and outward first headed towards its aphelion, against the present position of background stars, in the direction of Regulus in the constellation of Leo, as noted on February 26 and 27, 2009. It was expected to pass near Comet Cardinal on May 12, 2009.

Experiments have been flown by NASA, and SpaceX is developing large-scale on-orbit propellant transfer technology. Another approach to debris mitigation is to explicitly design the mission architecture to always leave the rocket second- stage in an elliptical geocentric orbit with a low-perigee, thus ensuring rapid orbital decay and avoiding long-term orbital debris from spent rocket bodies. Such missions will often complete the payload placement in a final orbit by the use of low-thrust electric propulsion or with the use of a small kick stage to circularize the orbit. The kick stage itself may be designed with the excess-propellant capability to be able to self-deorbit.

After a jet stream-related delay on 28 January 1958, at 10:48:16 PM Eastern Time on 31 January the Juno I rocket was launched, putting Explorer 1 into orbit with a perigee of and an apogee of having a period of 114.8 minutes. Goldstone Tracking Station could not report after 90 minutes as planned whether the launch had succeeded because the orbit was larger than expected. At about 1:30 a.m. ET, after confirming that Explorer 1 was indeed in orbit, a news conference was held in the Great Hall at the National Academy of Sciences in Washington, DC to announce it to the world.

Rusafi's literary critics, especially his inveterate adversary, Jalal al-Hanafi, in his book al- Rusafi fi awjih wa hadidih (Rusafi in his Apogee and Perigee), note that Rusafi gives colloquialism an unwarranted place both in his verse and prose. Khulusi believes that Rusafi is the only traditional, classical poet, in the Arabic language, who approved of both blank verse and free verse. His broad definition of poetry covers much that is regarded by classicists and purists as ornate prose, al-shi'r al-manthur (prose poetry). For Khulusi, Rusafi had a hypnotic manner in his recital with an overwhelming sense of the movement of the meter.

The rocket's second stage failed to provide the expected full thrust in all of its three burns due to a leak above the narrow throat portion of the thrust chamber, however the stage had enough propellant margins to put the satellite in the correct orbit. As of 18 February 2014, USA-232 was in an orbit with a perigee of , an apogee of , a period of 717.96 minutes, and 54.87 degrees of inclination to the equator. It is used to broadcast the PRN 24 signal, and operates in slot 1 of plane A of the GPS constellation. The satellite has a design life of 15 years and a mass of .

Less efficient departure times from the same depot to the same destination exist before and after the well-aligned opportunity, but more research is required to show whether the efficiency falls off quickly or slowly. By contrast, launching directly in only one launch from the ground without orbital refueling or docking with another craft already on orbit offers daily launch opportunities though it requires larger and more expensive launchers. The restrictions on departure windows arise because low earth orbits are susceptible to significant perturbations; even over short periods they are subject to nodal regression and, less importantly, precession of perigee. Equatorial depots are more stable but also more difficult to reach.

SMILE will be injected into a low Earth orbit by a Vega-C or Ariane 62 launcher from Kourou, French Guyana, and its propulsion module will bring the spacecraft to the nominal orbit with perigee altitude of around 5000 km. The SMILE spacecraft consists of a platform provided by the Chinese Academy of Sciences (CAS) attached to a payload module containing nearly all of the scientific instruments and an X-band communications system, provided by ESA. The payload module will be built by Airbus. The platform is composed of a propulsion and a service module, together with the two detectors (or heads) of the ion instrument.

GSAT-6A undergoing acoustic tests GSLV F08 launch from SLP GSLV-F08 carrying GSAT-6A spacecraft was launched from Second Launch Pad of Satish Dhawan Space Centre on 29 March 2018, 11:26 UTC and after flight of 17 minutes 45 seconds, placed GSAT-6A into its planned Geostationary transfer orbit with apogee, perigee and orbital inclination of 20.64°. GSAT-6A spacecraft deployed its solar array after separation from CUS and established contact with ground station. On GSLV-F08, a High Thrust Vikas engine (HTVE) was inducted on second stage (GS2) of GSLV with 6% higher thrust than before. The improved engine increased the payload capability of the vehicle.

INSAT 3C was launched by the Ariane 4 launch vehicle of Arianespace at 5:17 am IST from Kourou, French Guiana in South America. INSAT-3C was placed into a Geo-synchronous Transfer Orbit (GTO), 21 minutes after the lift-off, in a 3-axis stabilised mode, with a perigee of 570 km and an apogee of 35,920 km and an inclination of 4° with respect to the equator. After 4 maneuvers INSAT-3C has been put in its final three axis stabilised mode on February 1, 2002. The orbit rising maneuvers were carried out in phases by firing the 440 Newton Liquid Apogee Motor(LAM).

For a low Earth orbit, this velocity is about ; by contrast, the fastest manned airplane speed ever achieved (excluding speeds achieved by deorbiting spacecraft) was in 1967 by the North American X-15. The energy required to reach Earth orbital velocity at an altitude of is about 36 MJ/kg, which is six times the energy needed merely to climb to the corresponding altitude. Spacecraft with a perigee below about are subject to drag from the Earth's atmosphere, which decreases the orbital altitude. The rate of orbital decay depends on the satellite's cross-sectional area and mass, as well as variations in the air density of the upper atmosphere.

Some highly elliptical orbits may pass through the LEO region near their lowest altitude (or perigee) but are not in an LEO Orbit because their highest altitude (or apogee) exceeds . Sub-orbital objects can also reach the LEO region but are not in an LEO orbit because they re-enter the atmosphere. The distinction between LEO orbits and the LEO region is especially important for analysis of possible collisions between objects which may not themselves be in LEO but could collide with satellites or debris in LEO orbits. All crewed space stations to date, as well as the majority of satellites, have been in LEO.

Radiation more energetic than optical light, such as ultraviolet, X-rays, and gamma rays, and cannot penetrate Earth's atmosphere, direct observations must be made from space. INTEGRAL is an observatory, scientists can propose for observing time of their desired target regions, data are public after a proprietary period of up to one year. INTEGRAL was launched from the Russian Baikonur spaceport, in Kazakhstan. The 2002 launch aboard a Proton-DM2 rocket achieved a 3-day elliptical orbit with an apogee of nearly 160,000 km and a perigee of above 2,000 km, hence mostly beyond radiation belts which would otherwise lead to high instrumental backgrounds from charged-particle activation.

The Hindu calendar makes further rare adjustments, over a cycle of centuries, where a certain month is considered kshaya month (dropped). This occurs because of the complexity of the relative lunar, solar and earth movements. Underhill (1991) describes this part of Hindu calendar theory: "when the sun is in perigee, and a lunar month being at its longest, if the new moon immediately precedes a samkranti, then the first of the two lunar months is deleted (called nija or kshaya)." This, for example, happened in the year 1 BCE, when there was no new moon between Makara samkranti and Kumbha samkranti, and the month of Pausha was dropped.

The first space burial occurred in 1992 when the NASA (mission STS-52) carried a sample of Gene Roddenberry's cremated remains into space and returned them to Earth. The first private space burial, Celestis' Earthview 01: The Founders Flight, was launched on April 21, 1997. An aircraft departing from the Canary Islands carried a Pegasus rocket containing samples of the remains of 24 people to an altitude of above the Atlantic Ocean. The rocket then carried the remains into an elliptical orbit with an apogee of and a perigee of , orbiting the Earth once every 96 minutes until re-entry on May 20, 2002, northeast of Australia.

Ben Zimmer, "On Language: Crash Blossoms", New York Times Magazine, January 27, 2010 online text The Columbia Journalism Review regularly reprints such headlines in its "The Lower Case" column, and has collected them in the anthologies "Squad Helps Dog Bite Victim"Gloria Cooper, ed., Squad Helps Dog Bite Victim, and other flubs from the nation's press, Dolphin Books, 1980, and "Red Tape Holds Up New Bridge".Gloria Cooper, Red tape holds up new bridge, and more flubs from the nation's press, Perigee Books, 1987. Language Log also has an extensive archive of crash blossoms, for example "Infant Pulled from Wrecked Car Involved in Short Police Pursuit".

Extra fuel is required to compensate for the fact that the bursts take time; this is minimized by using high-thrust engines to minimize the duration of the bursts. For transfers in Earth orbit, the two burns are labelled the perigee burn and the apogee burn (or apogee kickJonathan McDowell, "Kick In the Apogee: 40 years of upper stage applications for solid rocket motors, 1957-1997", 33rd AIAA Joint Propulsion Conference, July 4, 1997. abstract. Retrieved 18 July 2017.); more generally, they are labelled periapsis and apoapsis burns. Alternately, the second burn to circularize the orbit may be referred to as a circularization burn.

In addition, the size of the penumbra is sometimes too small where the Moon enters it to contain the Moon. The width of the Earth's penumbra is determined by the Sun's angular diameter at the time of the eclipse, and the Moon's angular diameter is larger than the Sun over part of its elliptical orbit, depending on whether the eclipse occurs at the nearest (perigee) or farthest point (apogee) in its orbit around the Earth. The majority of the time, the size of the Moon and the size of the Earth's penumbra where the Moon crosses it mean that most eclipses will not be total penumbral in nature.

Perigee Books. . P.171. Edward Brophy (center) with Jackie Cooper and Wallace Beery in The Champ (1931) In 1928, with only a few minor film roles to his credit, Brophy was working as a junior production executive for Metro-Goldwyn-Mayer when he was chosen to appear with Buster Keaton in one sequence of Keaton's film The Cameraman. As two clients in a bath-house, Brophy and Keaton attempt to undress and put on bathing suits while sharing a single tiny changing room. Each time Keaton attempts to hang his clothes on one hook, Brophy removes the clothes and hands them back to Keaton and gestures to the other hook.

A total solar eclipse will occur on December 14, 2020. A solar eclipse occurs when the Moon passes between Earth and the Sun, thereby totally or partly obscuring the image of the Sun for a viewer on Earth. A total solar eclipse occurs when the Moon's apparent diameter is larger than the Sun's, blocking all direct sunlight, turning day into darkness. Totality occurs in a narrow path across Earth's surface, with the partial solar eclipse visible over a surrounding region thousands of kilometres wide. The Moon’s apparent diameter will be larger because the eclipse will occur only 1.8 days after perigee (on December 12, 2020).

Space Shuttle Discovery rockets to orbital velocity, seen here just after booster separation An orbital spaceflight (or orbital flight) is a spaceflight in which a spacecraft is placed on a trajectory where it could remain in space for at least one orbit. To do this around the Earth, it must be on a free trajectory which has an altitude at perigee (altitude at closest approach) around ; this is the boundary of space as defined by NASA, the US Air Force and the FAA. To remain in orbit at this altitude requires an orbital speed of ~7.8 km/s. Orbital speed is slower for higher orbits, but attaining them requires greater delta-v.

A total lunar eclipse took place on Thursday, October 28, 2004, the second of two total lunar eclipses in 2004, the first being on May 4, 2004.Hermit Eclipse: Saros cycle 136 It was the first lunar eclipse to take place during a World Series game, which when seen from Busch Memorial Stadium in St, Louis, Missouri, provided a surreal sight on the night the Boston Red Sox won their first World Series in 86 years to end the Curse of the Bambino. Occurring 5.6 days before apogee (Apogee on Tuesday, November 2, 2004), the Moon's apparent diameter was smaller. The moon was 10.1 days after perigee and 5.6 days before apogee.

Kosmos 1241 ( meaning Cosmos 1241) was a target satellite which was used by the Soviet Union in the 1980s for tests of anti-satellite weapons as part of the Istrebitel Sputnikov programme. It was launched in 1981, and was itself part of the Dnepropetrovsk Sputnik programme. It was a target for Kosmos 1243 and Kosmos 1258. It was launched at 08:29 UTC on 21 January 1981, using a Kosmos-3M carrier rocket, flying from Site 132/1 at the Plesetsk Cosmodrome in Northwest Russia. Kosmos 1241 was placed into a low Earth orbit with a perigee of , an apogee of , 65.8 degrees of inclination, and an orbital period of 105 minutes.

Elektrons 1 and 2 were launched on January 30, 1964, at 09:45:09 UTC from Launch Complex 1 at Baikonur Space Center (also known as NIIP-5) on a single Vostok 8K72K carrier rocket marking the first Soviet multiple satellite launch. The satellites, although launched from Earth together, were released at different stages, and so were able to achieve different orbits. The first satellite was released at a time when the upper stage of the launching rocket was still firing. Elektron 1's initial orbit had a perigee of , an apogee of , an orbital inclination of 61°, and a period of 169 minutes, an orbit that kept the satellite within Earth's Van Allen Belts.

Kosmos 605 was launched by a Soyuz-U rocket flying from Site 43/3 at the Plesetsk Cosmodrome in the Soviet Union. The satellite was initially launched in a low Earth orbit with a perigee of and a apogee with an orbital inclination of 62.8 degrees. The spacecraft orbited the Earth for 21 days until their biological capsule returned to Earth on 22 November 1973 in a region of northwestern present-day Kazakhstan. It carried several dozen male rats (possibly 25 or 45), six Russian tortoises (Agrionemys horsfieldii)Bion 1 Data Archive (each in a separate box), a mushroom bed, flour beetles (Tribolium confusum) in various stages of their life cycle, and living bacterial spores.

The satellite vehicle's Liquid Apogee Engine (LAE) provided by IHI failed to raise the orbit after two attempts. To solve the problem, the perigee altitude was raised to 4700 km with twelve firings of the smaller Aerojet Rocketdyne-provided Reaction Engine Assembly thrusters, originally intended for attitude control during the LAE engine burns. From this altitude, the solar arrays were deployed and the orbit was raised toward the operational orbit over the course of nine months using the 0.27 Newton Hall thrusters, also provided by Aerojet Rocketdyne, a form of electric propulsion which is highly efficient, but low thrust. This took much longer than initially intended due to the lower starting altitude for the HCT maneuvers.

The sixth burn of the SPS engine took place on the sixth day, though it was postponed one orbit as the reaction control system (RCS) thruster burn needed to settle the reactants in their tanks was not properly programmed. The SPS burn lowered the perigee of Apollo9's orbit, allowing for improved RCS thruster deorbit capability as a backup to the SPS. Gumdrop is hoisted aboard the USS Guadalcanal Considerable testing of the CSM took place, but this was principally Scott's responsibility, allowing McDivitt and Schweickart leisure to observe the Earth; they alerted Scott if anything particularly noteworthy was upcoming, letting him leave his work for a moment to look at Earth too.

Total energy balance during a Hohmann transfer between two circular orbits with first radius r_p and second radius r_a Consider a geostationary transfer orbit, beginning at r1 = 6,678 km (altitude 300 km) and ending in a geostationary orbit with r2 = 42,164 km (altitude 35,786 km). In the smaller circular orbit the speed is 7.73 km/s; in the larger one, 3.07 km/s. In the elliptical orbit in between the speed varies from 10.15 km/s at the perigee to 1.61 km/s at the apogee. Therefore the Δv for the first burn is 10.15 − 7.73 = 2.42 km/s, for the second burn 3.07 − 1.61 = 1.46 km/s, and for both together 3.88 km/s.

Soyuz TM-30 (, Union TM-30), also known as Mir EO-28, was a Soyuz mission, the 39th and final human spaceflight to the Mir space station. The crew of the mission was sent by MirCorp, a privately funded company, to reactivate and repair the station. The crew also resupplied the station and boosted the station to an orbit with a low point (perigee) of 360 and a high point (apogee) of 378 kilometers (223 and 235 miles, respectively). The boost in the station's orbit, which was done by utilizing the engines of the Progress M1-1 and M1-2 spacecraft, made transit between Mir and the International Space Station impossible, as desired by NASA.

The difference between two dates can be calculated by subtracting the Julian day number of one from that of the other, or there are simpler formulae giving (for instance) the number of days since December 31, 1899. However, this calculation assumes a perfectly circular orbit and makes no allowance for the time of day at which the new moon occurred and therefore may be incorrect by several hours. (It also becomes less accurate the larger the difference between the required date and the reference date). It is accurate enough to use in a novelty clock application showing lunar phase, but specialist usage taking account of lunar apogee and perigee requires a more elaborate calculation.

The Vostok 1 capsule when it was on display at the RKK Energiya museum. The main capsule, seen in the center of this picture, is now on display at the Space Pavilion at the VDNKh. At 07:25 UT, the spacecraft's automatic systems brought it into the required attitude (orientation) for the retrorocket firing, and shortly afterwards, the liquid-fueled engine fired for about 42 seconds over the west coast of Africa, near Angola, about uprange of the landing point. The orbit's perigee and apogee had been selected to cause reentry due to orbital decay within 10 days (the limit of the life support system function) in the event of retrorocket malfunction.

An annular solar eclipse occurred at the Moon's ascending node of the orbit on February 7, 2008. A solar eclipse occurs when the Moon passes between Earth and the Sun, thereby totally or partly obscuring the image of the Sun for a viewer on Earth. An annular solar eclipse occurs when the Moon's apparent diameter is smaller than the Sun's, blocking most of the Sun's light and causing the Sun to look like an annulus (ring). An annular eclipse appears as a partial eclipse over a region of the Earth thousands of kilometres wide. Occurring 7 days after apogee (January 31, 2008) and 6.9 days before perigee (February 14, 2008), the Moon’s apparent diameter was near the average diameter.

The groundtrack of QZSS orbit, which has similar characteristics to a Tundra orbit, but a lower inclination From 2000 to 2016, Sirius Satellite Radio, now part of Sirius XM Holdings, operated a constellation of three satellites in Tundra orbits for satellite radio. The RAAN and mean anomaly of each satellite were offset by 120° so that when one satellite moved out of position, another had passed perigee and was ready to take over. The constellation was developed to better reach consumers in far northern latitudes, reduce the impact of urban canyons and required only 130 repeaters compared to 800 for a geostationary system. After Sirius' merger with XM it changed the design and orbit of the FM-6 replacement satellite from a tundra to a geostationary one.

Using on-board propellant and lunar gravity, the orbit's apogee was gradually increased with several manoeuvres at perigee until it flew by the Moon at a distance of 6,200 km from its surface in May 1998, becoming in a sense the first commercial lunar spacecraft. Another lunar fly-by was performed later that month at a distance of 34,300 km to further improve the orbital inclination. These operations consumed most of the satellite's propellant, but still much less than it would take to remove the inclination without the Moon-assist manoeuvres. With the remaining fuel, the satellite could be controlled as a geosynchronous satellite, with half the life of a normal satellite – a huge gain, considering that it had been declared a total loss.

Its orbit is distinctly elliptic, so the lunar distance from Earth varies throughout the lunar cycle. This varying distance changes the apparent diameter of the Moon, and therefore influences the chances, duration, and type (partial, annular, total, mixed) of an eclipse. This orbital period is called the anomalistic month, and together with the synodic month causes the so-called "full moon cycle" of about 14 lunations in the timings and appearances of full (and new) Moons. The Moon moves faster when it is closer to the Earth (near perigee) and slower when it is near apogee (furthest distance), thus periodically changing the timing of syzygies by up to ±14 hours (relative to their mean timing), and changing the apparent lunar angular diameter by about ±6%.

It will be the fourth longest eclipse of the 21st century with a magnitude of 1.0774 occurring just one hour after perigee. It will be visible throughout much of the continental United States, with a path of totality running through northern California, Nevada, Utah, Colorado, Kansas, Oklahoma, Arkansas, Mississippi, Alabama, and Florida. The total eclipse will be greatest over the Bahamas, before continuing over the Turks and Caicos Islands, Cuba, Dominican Republic, Haiti, Venezuela, Trinidad and Tobago, Guyana, Suriname, French Guiana, and Brazil. The path of totality of this eclipse will be seen over many major cities, including Reno, Salt Lake City, Colorado Springs, Oklahoma City, Tulsa, Tampa, Orlando, Fort Lauderdale, Miami, Nassau, Santo Domingo, Belém, São Luís and Recife.

The transitive verb to Hawaiianize means to take a physical product, word, or concept hitherto unrelated to Hawaiian culture, and confer a Hawaiian form, quality, and character upon it through various means. The word is an increasingly popular neologism, in the manner of Anglicise, Africanise, and Americanize, and is most commonly used in matters of etymology and nomenclature."Hawaiian Baby Names," Baby Names OceanNorman, Teresa “A World of Baby Names,” See entry: Keli Published 2003, Perigee Consequently, it is used both to mean the transliteration of English into Hawaiian and also the general 'Hawaiianization' of anything. Hawaiianize "Hawaiianize ," KTC Hawaiian also means to incorporate the Hawaiian culture, spirit and character to anything and to live the Aloha Spirit through life, love and laughter.

Pyongyang claimed that Kwangmyŏngsŏng-2 was an experimental communications satellite as part of a peaceful space project. According to state news agency KCNA, which claimed the launch was successful, the satellite's orbital parameters consist of a perigee and apogee, with an orbital period of 104 minutes and 12 seconds and an orbital inclination of 40.6 degrees.Controversial satellite launch by North Korea triggers alarm, The Hindu, April 6, 2009 The satellite was said to have entered orbit nine minutes and two seconds after launch and began transmitting data and the "Song of General Kim Il-sung" and "Song of General Kim Jong-il" on a frequency of 470 MHz. However, similar claims were made in 1998 for Kwangmyŏngsŏng-1, whose launch attempt is believed to have failed.

The Skylab was launched into a quite different orbit, with a perigee which sustained it for six years, and also a higher inclination to the equator (50 degrees versus 32.5 degrees for Apollo). On Apollo 11, TLI came at 2 hours and 44 minutes after launch. The S-IVB burned for almost six minutes giving the spacecraft a velocity close to the Earth's escape velocity of . This gave an energy-efficient transfer to lunar orbit, with the Moon helping to capture the spacecraft with a minimum of CSM fuel consumption. About 40 minutes after TLI, the Apollo command and service module (CSM) separated from the third stage, turned 180 degrees, and docked with the Lunar Module (LM) that rode below the CSM during launch.

As the Minotaur V is a solid-propellant rocket, spacecraft attitude control on this mission operated a bit differently from a typical liquid-fueled rocket with more continuous closed-loop feedback. The first three Minotaur stages "fly a pre-programmed attitude profile" to gain velocity and deliver the vehicle to its preliminary trajectory, while the fourth stage is used to modify the flight profile and deliver the LADEE spacecraft into perigee for the spin-stabilized fifth stage to then put the spacecraft into a highly elliptical orbit around Earth—the first of three—to begin a month-long Lunar transit. While now separated from the LADEE spacecraft, both the fourth and fifth stages of the Minotaur V reached orbit, and are now space debris in Earth orbit.

His writings were influenced by Roger Bacon. At the end of the 13th century, Arnaldus de Villa Nova is credited with using a camera obscura to project live performances for entertainment. French astronomer Guillaume de Saint-Cloud suggested in his 1292 work Almanach Planetarum that the eccentricity of the sun could be determined with the camera obscura from the inverse proportion between the distances and the apparent solar diameters at apogee and perigee. Kamāl al-Dīn al-Fārisī (1267–1319) described in his 1309 work Kitab Tanqih al- Manazir (The Revision of the Optics) how he experimented with a glass sphere filled with water in a camera obscura with a controlled aperture and found that the colors of the rainbow are phenomena of the decomposition of light.

The totality of this eclipse was visible from northern Canada, Greenland, Norway, Sweden, Russian Empire (the parts now belonging to Åland Islands, Finland, Estonia, Latvia, Lithuania, Belarus, Ukraine and Russia, including cities of Riga, Minsk, Kiev and northeastern part of Vilnius), Ottoman Empire (the parts now belonging to Turkey, northeastern tip of Syria and northern Iraq), Persia and British Raj (the parts now belonging to Pakistan and western tip of India). It was the first of four total solar eclipses that would be seen from Sweden during the next 40 years. This total solar eclipse occurred in the same calendar date as 2017, but at the opposite node. The moon was just 2.7 days before perigee, making it fairly large.

The most commonly used orbits for both manned and unmanned space vehicles are low Earth orbits, which cover an altitude range low enough for residual atmospheric drag to be sufficient to help keep the zone clear. Collisions that occur in this altitude range are also less of an issue because the directions into which the fragments fly and/or their lower specific energy often result in orbits intersecting with Earth or having perigee below this altitude. Orbital decay is much slower at altitudes where atmospheric drag is insignificant. Slight atmospheric drag, lunar perturbation, and solar wind drag can gradually bring debris down to lower altitudes where fragments finally re-enter, but this process can take millennia at very high altitudes.

Chandrayaan-2's trajectory After being placed into a 45,475 × 169 km parking orbit by the launch vehicle, the Chandrayaan-2 spacecraft stack gradually raised its orbit using on-board propulsion over 22 days. In this phase, one perigee-raising and five apogee-raising burns were performed to reach a highly eccentric orbit of 142,975 × 276 km followed by trans-lunar injection on 13 August 2019. Such a long Earth-bound phase with multiple orbit-raising manoeuvres exploiting the Oberth effect was required because of the limited lifting capacity of the launch vehicle and thrust of the spacecraft's on-board propulsion system. A similar strategy was used for Chandrayaan-1 and the Mars Orbiter Mission during their Earth-bound phase trajectory.

Solar array power has gradually declined as the mission progressed, due to damage by energetic charged particles, but this was planned for and the power level remains sufficient for science operations. The four spacecraft maneuver into various tetrahedral formations to study the magnetospheric structure and boundaries. The inter- spacecraft distances can be altered and has varied from around 4 to 10,000 km. The propellant for the transfer to the operational orbit, and the maneuvers to vary inter-spacecraft separation distances made up approximately half of the spacecraft's launch weight. The highly elliptical orbits of the spacecraft initially reached a perigee of around 4 RE (Earth radii, where 1 RE = 6371 km) and an apogee of 19.6 RE. Each orbit took approximately 57 hours to complete.

PSLV C11 carrying Chandrayaan-1 During the tenure Prime Minister Manmohan Singh chandrayan project got a boost and finally Chandrayaan-1 was launched on 22 October 2008 at 00:52 UTC from Satish Dhawan Space Centre using the ISRO's tall, four-stage PSLV C11 launch vehicle. Chandrayaan-1 was sent to the Moon in a series of orbit-increasing manoeuvres around the Earth over a period of 21 days as opposed to launching the craft on a direct trajectory to the Moon. At launch the spacecraft was inserted into geostationary transfer orbit (GTO) with an apogee of and a perigee of . The apogee was increased with a series of five orbit burns conducted over a period of 13 days after launch.

Launched on June 15, 1963 (COSPAR 1963-021C) via a Thor Augmented Delta-Agena D rocket from Vandenberg AFB with four other satellites, SOLRAD 6 was placed into an incorrect elliptical orbit, its perigee so low that the atmosphere soon caused the satellite to decay from orbit on July 31, 1963. Because of its short orbital lifetime, SOLRAD 6 returned relatively little data. Moreover, the Sun was very quiet during the satellite's six weeks of operation, and the four Lyman-Alpha photometers capable of registering X-ray emissions with wavelengths shorter than 8Å reported no results. No scientific data were ever published from SOLRAD 6's measurements, and the strip chart recordings of them were no longer available as of 1991.

Salyut 4 (DOS 4) (; English translation: Salute 4) was a Salyut space station launched on December 26, 1974 into an orbit with an apogee of 355 km, a perigee of 343 km and an orbital inclination of 51.6 degrees. It was essentially a copy of the DOS 3 (or Kosmos 557), and unlike its ill-fated sibling it was a complete success. Three crews attempted to make stays aboard Salyut 4 (Soyuz 17 and Soyuz 18 docked; Soyuz 18a suffered a launch abort). The second stay was for 63 days duration, and an unmanned capsule, called Soyuz 20, remained docked to the station for three months, proving the system's long-term durability despite some deterioration of the environmental system during Soyuz 18's mission.

NASA art for a concept combining three technologies: electromagnetic launch assist from a hypothetical track at Kennedy Space Center, a scramjet aircraft, and a carried rocket for use after air launch reaches orbit. Separate technologies may be combined. In 2010, NASA suggested that a future scramjet aircraft might be accelerated to 300 m/s (a solution to the problem of ramjet engines not being startable at zero airflow velocity) by electromagnetic or other sled launch assist, in turn air- launching a second-stage rocket delivering a satellite to orbit. All forms of projectile launchers are at least partially hybrid systems if launching to low Earth orbit, due to the requirement for orbit circularization, at a minimum entailing several percent of total delta-v to raise perigee (e.g.

In all cases, once initial deceleration has lowered the orbital perigee into the mesosphere, all spacecraft lose most of the remaining speed, and therefore kinetic energy, through the atmospheric drag effect of aerobraking. Intentional aerobraking is achieved by orienting the returning space craft so as to present the heat shields forward toward the atmosphere to protect against the high temperatures generated by atmospheric compression and friction caused by passing through the atmosphere at hypersonic speeds. The thermal energy is dissipated mainly by compression heating the air in a shockwave ahead of the vehicle using a blunt heat shield shape, with the aim of minimising the heat entering the vehicle. Sub-orbital space flights, being at a much lower speed, do not generate anywhere near as much heat upon re-entry.

With the warhead back in their possession, and the timing and location of the comet's overhead passing accurately calculated by Dr. Kim, the "Heavenly Soldiers" prepare to leave the past as it currently stands. Yi, incensed by the barbarians' cruelty, returns to the modern Koreans with their weapons and the elders of the girl's village, who plead with the "Heavenly Soldiers" to help them, and the modern Koreans relent. When Majors Park and Kang debate over the strategy that would work best for the villagers, Yi, beginning to find his legendary tactical competence, successfully argues for a combination of ambushes and a last stand. That night, before the arrival of the Jurchens, the modern Koreans prepare to leave the past, as the comet would unexpectedly perigee later the next day.

His publications, in eleven different languages, include 131 scientific papers, 20 book chapters and 14 books, including Pursuing the Birth Machine (1994),Marsden Wagner, Pursuing the Birth Machine: The Search for Appropriate Birth Technology, Camperdown, New South Wales: ACE Graphics, 1994, . credited with creating a social model of birth,Denis Walsh and Mary Newburn, "Towards a social model of childbirth: part one", British Journal of Midwifery 10(8) August 9, 2002:476-81. and Creating Your Birth Plan (2006)Marsden Wagner with Stephanie Gunning, Creating Your Birth Plan: The Definitive Guide to a Safe and Empowering Birth, New York: Perigee, 2006, . His Born in the USA (2006)Marsden Wagner, Born in the USA: How a Broken Maternity System Must Be Fixed to Put Women and Children First, Berkeley: University of California, 2006, .

Developed under the working title The Julie Brown Show, it also starred Marian Mercer as Julie's mother, June; DeLane Matthews as Debra Deacon, a reporter on the fictional series Inside Scoop; Susan Messing as Julie's roommate Cheryl; and Kevin O'Rourke as Inside Scoop producer Tony Barnow. Brown was also a producer, with John Ziffren, and performed and co-wrote the theme song. Walker, Don Sparks, Robin Angers, and Deborah Driggs were guest performers in this production from Mirkinvision and New World Television.Lovece, Frank. The Television Yearbook 1990-91 (Perigee Books / Putnam Publishing, 1991), p. 267 Another pilot was filmed for CBS, Julie Brown: The Show, and featured a similar theme, in which Brown was the hostess of a talk show and she would interview actual celebrity guests, interspersed with scripted scenarios.

The mission was given the go-ahead by ESA in 1980, and launched on an Ariane 1 rocket (flight V14) on 2 July 1985 from Kourou, French Guiana. The craft was controlled from the European Space Agency ESOC facilities in Darmstadt (then West Germany) initially in Geostationary Transfer Orbit (GTO) then in the Near Earth Phase (NEP) before the longer Cruise Phase through to the encounter. While in GTO a number of slew and spin-up manoeuvres (to 90 RPM) were carried out in preparation for the firing of the Apogee Boost Motor (ABM), although unlike orbit circularisations for geostationary orbit, the ABM for Giotto was fired at perigee. Attitude determination and control used sun pulse and IR Earth sensor data in the telemetry to determine the spacecraft orientation.

The satellites initially received the name of Brasilsat 1 and 2 and formed the beginning of the Brazilian Telecommunications Satellite System - SBTS. Subsequently, with the launch of the second generation of satellites, they were renamed Brasilsat-A1 and A2, and were replaced by the satellites Brasilsat B1 and Brasilsat B2. The Brasilsat A2 satellite was the second Brazilian satellite owned by the former state-owned Embratel, which was privatized on March 28, 1986, by a 2/3 Ariane rocket at Kourou's launch base in French Guiana. This satellite was equal to Brasilsat A1. It had a mass at the launch of 1,243 kg, Perigee of 35,778 km, Apogee of 35,794 km and a slope of 0.0 degrees. During its commercial life, it was parked at 70 degrees west.

This longer period is called the anomalistic month and has an average length of days (27 d 13 h 18 m 33.2 s). The apparent diameter of the Moon varies with this period, so this type has some relevance for the prediction of eclipses (see Saros), whose extent, duration, and appearance (whether total or annular) depend on the exact apparent diameter of the Moon. The apparent diameter of the full moon varies with the full moon cycle, which is the beat period of the synodic and anomalistic month, as well as the period after which the apsides point to the Sun again. An anomalistic month is longer than a sidereal month because the perigee moves in the same direction as the Moon is orbiting the Earth, one revolution in nine years.

The satellite was successfully launched, along with the Herschel Space Observatory, at 13:12:02 UTC on 14 May 2009 aboard an Ariane 5 ECA heavy launch vehicle from the Guiana Space Centre. The launch placed the craft into a very elliptical orbit (perigee: , apogee: more than ), bringing it near the Lagrangian point of the Earth-Sun system, from the Earth. The manoeuvre to inject Planck into its final orbit around was successfully completed on 3 July 2009, when it entered a Lissajous orbit with a radius around the Lagrangian point. The temperature of the High Frequency Instrument reached just a tenth of a degree above absolute zero (0.1 K) on 3 July 2009, placing both the Low Frequency and High Frequency Instruments within their cryogenic operational parameters, making Planck fully operational.

NASA maintains an automated system to evaluate the threat from known NEOs over the next 100 years, which generates the continuously updated Sentry Risk Table. All or nearly all of the objects are highly likely to drop off the list eventually as more observations come in, reducing the uncertainties and enabling more accurate orbital predictions. In March 2002, became the first asteroid with a temporarily positive rating on the Torino Scale, with about a 1 in 9,300 chance of an impact in 2049. Additional observations reduced the estimated risk to zero, and the asteroid was removed from the Sentry Risk Table in April 2002. It is now known that in the next two centuries, will pass the Earth at a safe closest distance (perigee) of on August 31, 2080.

USA-214 was launched by United Launch Alliance, using an Atlas V 531 carrier rocket flying from Space Launch Complex 41 at the Cape Canaveral Air Force Station. The launch occurred at 11:07 UTC on 14 August 2010, and resulted in the spacecraft being deployed successfully into a geosynchronous transfer orbit with a perigee of , an apogee of , and 22.2° inclination. The spacecraft was intended to manoeuvre from the transfer orbit into which it was launched to its operational geosynchronous orbit by means of a Liquid Apogee Engine (LAE) and several Hall effect thrusters, a process which normally takes 105 days. However, the satellite's Liquid Apogee Engine malfunctioned shortly after ignition on both its first burn on 15 August 2010 and a second attempt on 17 August,Ray, Justin (Sept.

The U.S. Air Force has stated that the X-37B is testing a Hall-effect thruster system for Aerojet Rocketdyne. In July 2019, former United States Secretary of the Air Force Heather Wilson explained that when an X-37B was in an elliptic orbit it could at perigee use the thin atmosphere to make an orbit change preventing some observers from discovering the new orbit for a while, permitting secret activities. Astronomer Jonathan McDowell, editor of Jonathan's Space Report, has stated that satellites launched from the X-37B were not reported, as required by the Registration Convention, to the United Nations Office for Outer Space Affairs so other parties to the convention would not know about them. The Chinese Space Program landed its first reusable winged space plane on 6 September 2020.

A Proton-K carrier rocket successfully put the spacecraft and a Blok D upper stage into a low earth parking orbit with an apogee of and a perigee of and an inclination of 51.4 degrees. The Blok D's ignition timer was incorrectly set, resulting in it failing to ignite; the timer had been set so that the stage would ignite 1.5 years after launch rather than the intended 1.5 hours. Due to its low orbit, which quickly decayed, Kosmos 419 reentered the Earth's atmosphere on 12 May 1971, two days after launch. The designation Kosmos 419 was a generic name given to Soviet spacecraft operating in Earth orbit; at the time Soviet planetary spacecraft which failed to depart Earth orbit would be given designations in the Kosmos series to disguise the failure.

A rocket can be used for additional boost, as planned in both Project HARP and the Quicklaunch project. The magnitude of such correction may be small; for instance, the StarTram Generation 1 reference design involves a total of of rocket burn to raise perigee well above the atmosphere when entering an low Earth orbit. In a three-body or larger system, a gravity assist trajectory might be available such that a carefully aimed escape velocity projectile would have its trajectory modified by the gravitational fields of other bodies in the system such that the projectile would eventually return to orbit the initial planet using only the launch delta-v. Isaac Newton avoided this objection in his thought experiment by positing an impossibly tall mountain from which his cannon was fired.

The spacecraft was launched, on 23 February 1999 at 10:29:55 UTC, from the Vandenberg Air Force Base SLC-2W pad, as an auxiliary payload into a near-sun synchronous elliptical polar orbit, it had a perigee of , an apogee of , an inclination of 96.1, and an orbital period of 100.0 minutes, and nodal drift rate 0.76°/day. It is gravity- gradient stabilized, with its extendable boom aligned to and pointing away from the center of the Earth. Active attitude control is achieved using three- axis magnetic torquing coils. The data system features onboard monitoring and pre-processing. Data is stored in a 16 Mbyte on-board memory and downlinked in a packetized format when a ground station is in view. In 2010, Ørsted passed within 500 meters of debris from the 2009 satellite collision but suffered no damage.terma.

Long March 2 was the original model in the Long March 2 rocket family, which was derived from China's first ICBM, the DF-5. The development work began in 1970. The first rocket was launched on November 5, 1974, but the launch failed. After the failed first launch of Long March 2, its design was slightly modified and designated as Long March 2A. Long March 2A was successfully launched in 1975. The production of the Long March 2A ended in 1979. Long March 2C and Long March 2D's first launches occurred in 1982 and 1992 respectively. The Long March 2E was the first in the Long March rocket family to introduce liquid rocket boosters, as well as a solid rocket perigee kick stage, to improve its GTO payload capacity to satisfy the domestic and international launch market in the 1990s.

The Combined Release and Radiation Effects Satellite (CRRES) was launched on July 25, 1990, into a geosynchronous transfer orbit (GTO) for a nominal three- year mission to investigate fields, plasmas, and energetic particles inside the Earth's magnetosphere. As part of the CRRES program, the SPACERAD (Space Radiation Effects) project, managed by Air Force Geophysics Laboratory, investigated the radiation environment of the inner and outer radiation belts and measured radiation effects on state-of-the-art microelectronics devices. CRRES aboard Atlas I Other magnetospheric, ionospheric, and cosmic ray experiments were also included onboard CRRES and supported by NASA or the Office of Naval Research. The chemical release project was managed by NASA/MSFC and utilized the release of chemicals from onboard canisters at low altitudes near dawn and dusk perigee times and at high altitudes near local midnight.

Though the resolution of satellite photographs, which must be taken from distances of hundreds of kilometers, is usually poorer than photographs taken by air, satellites offer the possibility of coverage for much of the earth, including hostile territory, without exposing human pilots to the risk of being shot down. Ground-resolution distance achieved by KH-8 There have been hundreds of reconnaissance satellites launched by dozens of nations since the first years of space exploration. Satellites for imaging intelligence were usually placed in high-inclination low Earth orbits, sometimes in Sun-synchronous orbits. Since the film-return missions were usually short, they could indulge in orbits with low perigees, in the range of 100–200 km, but the more recent CCD- based satellites have been launched into higher orbits, 250–300 km perigee, allowing each to remain in orbit for several years.

One particular supersynchronous orbital regime of significant economic value to Earth commerce is a band of near-circular Geocentric orbits beyond the Geosynchronous belt—with perigee altitude above , approximately above synchronous altitude —called the geo graveyard belt. The geo graveyard belt orbital regime is valuable as a storage and disposal location for derelict satellite space debris after their useful economic life is completed as geosynchronous communication satellites. Artificial satellites are left in space because the economic cost of removing the debris would be high, and current public policy does not require nor incentivize rapid removal by the party that first inserted the debris in outer space and thus created a negative externality for others—a placing of the cost onto them. One public policy proposal to deal with growing space debris is a "one-up/one-down" launch license policy for Earth orbits.

In astronomy, evection (Latin for "carrying away") is the largest inequality produced by the action of the Sun in the monthly revolution of the Moon around the Earth. The evection, formerly called the moon's second anomaly, was approximately known in ancient times, and its discovery is attributed to Ptolemy.Neugebauer, 1975. The current name itself dates much more recently, from the 17th century: it was coined by Bullialdus in connection with his own theory of the Moon's motion.R Taton & C Wilson, 1989 Evection causes the Moon's ecliptic longitude to vary by approximately ± 1.274° (degrees), with a period of about 31.8 days. The evection in longitude is given by the expression +4586.45\sin (2D-\ell), where D is the mean angular distance of the Moon from the Sun (its elongation), and \ell is the moon's mean angular distance of the moon from its perigee (mean anomaly).

Elektron 2 and 4 had design masses of , were in diameter and long, also cylindrical, but with a skirt of solar cells with a combined area of 20 m2 for power generation rather than solar panels. The satellites were to be boosted into highly eccentric × orbits to map the outer Van Allen belt while, simultaneously, Elektron 1 and 3 probed the inner radiation belt. To achieve this orbit, Elektron 2 and 4 were each equipped with solid-propellant perigee kick motor of 3,350 kgf and 12 to 15 seconds duration. The experiment packages for Elektron 2 and 4 were also identical and each included a radio frequency mass spectrometer; Geiger counters, scintillation counters, and semiconductor detectors for radiation studies; a spherical ion trap; two three-axis fluxgate magnetometers; a galactic radio-noise receiver; solar X-ray photometers; and a Cerenkov-scintillator cosmic-ray telescope.

The purpose of the Explorer 54 was to continue the investigation begun by Explorer 51 (AE-C) of the chemical processes and energy transfer mechanisms that control the structure and behavior of the earth's atmosphere and ionosphere in the region of high absorption of solar energy. This mission was planned to sample the high latitude regions at the same time that the Explorer 55 (AE-E) mission was sampling the equatorial and low latitude regions. The same type of spacecraft as Explorer 54 was used, and the payload consisted of the same types of instruments except for deletion of the extreme solar UV monitor and the Bennett ion mass spectrometer, which were part of the Explorer 55 payload. The polar orbit provided the sampling of all latitudes and the perigee moved through all latitudes in 3 months and all local times in 4 months.

Intelsat 605, previously named Intelsat VI F-5, was a communications satellite operated by Intelsat. Launched in 1991, it was the fourth of five Intelsat VI satellites to be launched. The Intelsat VI series was constructed by Hughes Aircraft, based on the HS-389 satellite bus. Intelsat 605 was launched at 23:15:13 UTC on 14 August 1991, atop an Ariane 4 44L carrier rocket, flight number V45. The launch took place from ELA-2 at Kourou, and placed Intelsat 605 into a geosynchronous transfer orbit. The satellite raised itself into its final geostationary orbit using two liquid-fuelled R-4D-12 engines, with the satellite arriving in geostationary orbit on 20 August 1991. Intelsat 605 initially operated in a geostationary orbit with a perigee of , an apogee of , and 0 degrees of inclination. The satellite carried 38 IEEE C band and ten IEEE transponders, and had a design life of 13 years and a mass of .

Graph showing the changing altitude of Mir from 19 February 1986 until 21 March 2001 Mir was maintained in a near circular orbit with an average perigee of and an average apogee of , travelling at an average speed of 27,700 km/h (17,200 mph) and completing 15.7 orbits per day. As the station constantly lost altitude because of slight atmospheric drag, it needed to be boosted to a higher altitude several times each year. This boost was generally performed by Progress resupply vessels, although during the Shuttle-Mir programme the task was performed by US Space Shuttles, and, prior to the arrival of Kvant-1, the engines on the core module could also accomplish the task. Attitude control was maintained by a combination of two mechanisms; in order to hold a set attitude, a system of twelve control moment gyroscopes (CMGs, or "gyrodynes") rotating at 10,000 rpm kept the station oriented, six CMGs being located in each of the Kvant-1 and Kvant-2 modules.

Kosmos 2421 (Cosmos 2421) was a Russian spy satellite launched in 2006, but began fragmenting in early 2008.Orbital Debris Quarterly News - Volume 12 Issue 3 It also had the Konus-A gamma-ray burst experiment by Ioffe Institute.russianspaceweb Three separate fragmentation events produced about 500 pieces of trackable debris, but about half of those had already re-entered by the fall of 2008.Cosmos 2421 The International Space Station adjusted its orbit to avoid debris fragment 33246 from the Kosmos 2421 breakup.Orbital Debris Quarterly News - Volume 12 Issue 4 That piece was predicted to have a 1 in 72 chance of hitting the station without a change. Kosmos 2421 was in a higher orbit than ISS, so when ISS's apogee (high point of orbit) surpassed the debris field's perigee (low point of orbit), many fragments would cross ISS's orbit. Kosmos 2421 was launched on June 25, 2006 on a Tsyklon-2 from LC90 at Baykonur.Cosmos 2421 Other designations are 2006-026A and NORAD 29247.

"NORTH KOREAN CONSULAR OFFICIAL IN RUSSIA MAKES COMMENT ON MISSILE LAUNCH", ITAR-TASS news agency (World Service), Moscow, 2 September 1998 The DPRK Socialist Constitution declared Kim Il-sŏng "eternal president of the DPRK" and elevated the status of the National Defense Commission, which is chaired by Kim Chŏng-il. In the days before and after the attempted satellite launch, DPRK media often made references to the doctrine of Kangsŏngdaeguk (national strength and prosperity) since satellite launches and missiles represent the highest levels of technology. On 13 September, the North Korean media reported that the satellite had completed its 100th orbit, and that it was in an elliptical medium Earth orbit with a perigee of and apogee of with a period of 165 minutes and 6 seconds. North Korea stated that the satellite carried transmitters which broadcast the "Song of General Kim Il-sung", the "Song of General Kim Jong-il" and "Juche Korea" in morse code, on a frequency of 27 MHz.

An eclipse does not happen at every new or full moon, because the plane of the orbit of the Moon around the Earth is tilted with respect to the plane of the orbit of the Earth around the Sun (the ecliptic): so as seen from the Earth, when the Moon is nearest to the Sun (new moon) or at largest distance (full moon), the three bodies usually are not exactly on the same line. This inclination is on average about 5° 9′, much larger than the apparent mean diameter of the Sun (32′ 2″), the Moon as seen from the surface of the Earth right beneath the Moon (31′ 37″), and the shadow of the Earth at the mean lunar distance (1° 23′). Therefore, at most new moons the Earth passes too far north or south of the lunar shadow, and at most full moons the Moon misses the shadow of the Earth. Also, at most solar eclipses the apparent angular diameter of the Moon is insufficient to fully obscure the solar disc, unless the Moon is near its perigee, i.e.

It was first proposed by Apollonius of Perga at the end of the 3rd century BC. It was developed by Apollonius of Perga and Hipparchus of Rhodes, who used it extensively, during the 2nd century BC, then formalized and extensively used by Ptolemy of Thebaid in his 2nd century AD astronomical treatise the Almagest. Epicyclical motion is used in the Antikythera mechanism, an ancient Greek astronomical device for compensating for the elliptical orbit of the Moon, moving faster at perigee and slower at apogee than circular orbits would, using four gears, two of them engaged in an eccentric way that quite closely approximates Kepler's second law. Epicycles worked very well and were highly accurate, because, as Fourier analysis later showed, any smooth curve can be approximated to arbitrary accuracy with a sufficient number of epicycles. However, they fell out of favour with the discovery that planetary motions were largely elliptical from a heliocentric frame of reference, which led to the discovery that gravity obeying a simple inverse square law could better explain all planetary motions.

USA-94, also known as GPS IIA-13, GPS II-22 and GPS SVN-35, was an American navigation satellite which formed part of the Global Positioning System. It was the thirteenth of nineteen Block IIA GPS satellites to be launched. USA-94 was launched at 12:38:00 UTC on 30 August 1993, atop a Delta II carrier rocket, flight number D222, flying in the 7925-9.5 configuration. The launch took place from Launch Complex 17B at the Cape Canaveral Air Force Station, and placed USA-94 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. On 1 October 1993, USA-94 was in an orbit with a perigee of , an apogee of , a period of 718 minutes, and 54.8 degrees of inclination to the equator. It broadcast the PRN 30 signal, and operated in slot 4, and later 5, of plane B of the GPS constellation. The satellite had a mass of and a design life of 7.5 years.

The launch of STS-32 from LC-39A. The Syncom IV-F5 satellite is deployed. , returning to Kennedy Space Center (KSC) after the successful STS-32 mission, flies past the Vehicle Assembly Building at KSC, secured atop the Shuttle Carrier Aircraft. STS-32 launched from Kennedy Space Center (KSC), Florida, on 9 January 1990 at 7:35:00 am EST. The launch was initially scheduled for 18 December 1989, but was later postponed to allow the modifications to Pad A to be completed and verified. The second scheduled launch, on 8 January 1990, was aborted due to weather conditions. Columbia had a mission launch weight of The primary objectives of the mission were to deploy the Syncom IV-F5 defense communications satellite (also known as Leasat 5), and to retrieve NASA's Long Duration Exposure Facility (LDEF), whose retrieval had been delayed for 4 years by scheduling changes and the Challenger disaster of 1986. Syncom IV-F5 was deployed on the second flight day, and a third-stage Minuteman solid perigee kick motor propelled it into a geosynchronous orbit.

The European X-ray Observatory Satellite (EXOSAT), originally named HELOS, was an X-ray telescope operational from May 1983 until April 1986 and in that time made 1780 observations in the X-ray band of most classes of astronomical object including active galactic nuclei, stellar coronae, cataclysmic variables, white dwarfs, X-ray binaries, clusters of galaxies, and supernova remnants. This European Space Agency (ESA) satellite for direct-pointing and lunar-occultation observation of X-ray sources beyond the solar system was launched into a highly eccentric orbit (apogee 200,000 km, perigee 500 km) almost perpendicular to that of the moon on 26 May 1983. The instrumentation includes two low-energy imaging telescopes (LEIT) with Wolter I X-ray optics (for the 0.04–2 keV energy range), a medium-energy experiment using Ar/CO2 and Xe/CO2 detectors (for 1.5–50 keV), a Xe/He gas scintillation spectrometer (GSPC) (covering 2–80 keV), and a reprogrammable onboard data-processing computer. Exosat was capable of observing an object (in the direct-pointing mode) for up to 80 hours and of locating sources to within at least 10 arcsec with the LEIT and about 2 arcsec with GSPC.

Westars 1, 2 and 3 were built by Hughes using the HS 333 platform of spin-scan stabilized satellites. They only had 12 transponders on board, as opposed to later C-band communications satellites having 24, and even contemporary satellites of the same era, such as RCA's Satcom 1. Westar 6 retrieval by Astronaut Dale Gardner The later Westar 4 (launched on February 26, 1982) and Westar 5 (launched on June 9, 1982) satellites, were based on the Hughes HS 376 platform, and had 24 transponders available, as opposed to the 12 on Westars 1, 2, and 3. Westar 6, also an HS-376 based satellite, was launched from STS-41-B on February 3, 1984, to be put into service afterward, but the perigee kick motor (also known as the Payload Assist Module, or PAM) on the satellite failed during its approach to geosynchronous orbit, placing it at an improper and inoperable low Earth orbit. It was retrieved on November 16, 1984, by the STS-51-A mission of NASA's Space Shuttle, where it was brought back to earth. It was then resold to AsiaSat in Hong Kong, who refurbished it and relaunched it on April 7, 1990 as AsiaSat 1.

Sputnik 41 (, ), also known as Sputnik Jr 2 and Radio Sputnik 18 (RS-18), was a Franco-Russian amateur radio satellite which was launched in 1998 to commemorate the hundredth anniversary of the Aéro-Club de France, and the forty-first anniversary of the launch of Sputnik 1, the world's first artificial satellite. A one-third scale model of Sputnik 1, Sputnik 41 was deployed from the Mir space station on 10 November 1998. Sputnik 41 was launched aboard Progress M-40 at 04:14 UTC on 25 October 1998, along with supplies for Mir and the Znamya-2.5 reflector experiment. A Soyuz-U carrier rocket placed the spacecraft into orbit, flying from Site 1/5 at the Baikonur Cosmodrome in Kazakhstan: the same launch pad used by Sputnik 1. Progress M-40 docked to Mir on 27 October, and the satellite was transferred to the space station. At about 19:30 UTC on 10 November, during an extra-vehicular activity, Sputnik 41 was deployed by cosmonauts Gennady Padalka and Sergei Avdeyev. On 24 November, a fortnight after deployment, Sputnik 41 was in a low Earth orbit with a perigee of , an apogee of , an inclination of 51.6 degrees, and a period of 91.44 minutes. The satellite was given the International Designator 1998-062C, and was catalogued by the United States Space Command as 25533.