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USA-71
USA-71, also known as GPS IIA-2, GPS II-11 and GPS SVN-24, is an American navigation satellite which forms part of the Global Positioning System. It was the second of nineteen Block IIA GPS satellites to be launched. USA-71 was launched at 02:32:00 UTC on 4 July 1991, atop a Delta II carrier rocket, flight number D206, flying in the 7925-9.5 configuration.[3] The rocket launched from Launch Complex 17A at the Cape Canaveral Air Force Station,[5] and placed USA-71 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor.[2] On 14 August 1991, USA-71 was in an orbit with a perigee of 20,085 kilometres (12,480 mi), an apogee of 20,274 kilometres (12,598 mi), a period of 717.86 minutes, and 55.1 degrees of inclination to the equator.[4] It has PRN 24, and operated in slot 1 of plane D of the GPS constellation[6] until it was removed from service in September 2009
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Navigation Satellite
A satellite navigation or satnav system is a system that uses satellites to provide autonomous geo-spatial positioning. It allows small electronic receivers to determine their location (longitude, latitude, and altitude/elevation) to high precision (within a few metres) using time signals transmitted along a line of sight by radio from satellites. The system can be used for providing position, navigation or for tracking the position of something fitted with a receiver (satellite tracking). The signals also allow the electronic receiver to calculate the current local time to high precision, which allows time synchronisation. Satnav systems operate independently of any telephonic or internet reception, though these technologies can enhance the usefulness of the positioning information generated. A satellite navigation system with global coverage may be termed a global navigation satellite system (GNSS)
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Semi-synchronous Orbit
A semi-synchronous orbit is an orbit with a period equal to half the average rotational period of the body being orbited, and in the same direction as that body's rotation. For Earth, a semi-synchronous orbit is considered a medium Earth orbit, with a period of just under 12 hours. For circular Earth orbits, the altitude is approximately 20,200 kilometres (12,600 mi).[1][2] Semi-synchronous orbits are typical for GPS satellites. See also[edit]Molniya orbit List of orbitsReferences[edit]^ "NASA Technical Standard 8719.14 (draft)". NASA Orbital Debris Program Office. 8 Aug 2006. Archived from the original (PDF) on 2006-08-23.  ^ "Catalog of Earth
Earth
Satellite Orbits"
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Encyclopedia Astronautica
The Encyclopedia Astronautica is a reference web site on space travel. A comprehensive catalog of vehicles, technology, astronauts, and flights, it includes information from most countries that have had an active rocket research program, from Robert Goddard to the NASA
NASA
Space shuttle to the Soviet Shuttle Buran. It is maintained by space enthusiast and author Mark Wade.[2] He has been collecting such information for most of his life. See also[edit]Jonathan's Space Report List of online encyclopediasReferences[edit]^ "Astronautix.com Site Info". Alexa Internet. Retrieved 2017-07-13.  ^ David J. Shayler (2001). Gemini - Steps to the Moon. Springer Science+Business Media. p. 386. ISBN 978-1-85233-405-5. External links[edit]Official websiteThis space- or spaceflight-related article is a stub
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Inclination
Orbital inclination
Orbital inclination
measures the tilt of an object's orbit around a celestial body. It is expressed as the angle between a reference plane and the orbital plane or axis of direction of the orbiting object. For a satellite orbiting the Earth
Earth
directly above the equator, the plane of the satellite's orbit is the same as the Earth's equatorial plane, and the satellite's orbital inclination is 0°. The general case for a circular orbit is that it is tilted, spending half an orbit over the northern hemisphere and half over the southern
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Apogee Motor
An apogee kick motor (AKM) refers to a rocket motor that is regularly employed on artificial satellites to provide the final impulse to change the trajectory from the transfer orbit into its final (most commonly circular) orbit. For a satellite launched from the Earth, the rocket firing is done at the highest point of the transfer orbit, known as the apogee, thus giving the engine its name. An apogee kick motor is used, for example, for satellites launched into a geostationary orbit. As the vast majority of geostationary satellite launches are carried out from spaceports at a significant distance away from Earth's equator, the carrier rocket often only launches the satellite into an orbit with a non-zero inclination approximately equal to the latitude of the launch site. This orbit is commonly known as a "geostationary transfer orbit" or a "geosynchronous transfer orbit". The satellite must then provide thrust to bring forth the needed delta v to reach a geostationary orbit
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United States
Coordinates: 40°N 100°W / 40°N 100°W / 40; -100 United States
United States
of AmericaFlagGreat SealMotto:  "In God
God
We Trust"[1][fn 1]Other traditional mottos  "E pluribus unum" (Latin) (de facto) "Out of many, one" "Annuit cœptis" (Latin) "He h
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Orbital Period
The orbital period is the time a given astronomical object takes to complete one orbit around another object, and applies in astronomy usually to planets or asteroids orbiting the Sun, moons orbiting planets, exoplanets orbiting other stars, or binary stars. For objects in the Solar System, this is often referred to as the sidereal period, determined by a 360° revolution of one celestial body around another, e.g. the Earth
Earth
orbiting the Sun. The name sidereal is added as it implies that the object returns to the same position relative to the fixed stars projected in the sky. When describing orbits of binary stars, the orbital period is usually referred to as just the period
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Orbital Inclination
Orbital inclination
Orbital inclination
measures the tilt of an object's orbit around a celestial body. It is expressed as the angle between a reference plane and the orbital plane or axis of direction of the orbiting object. For a satellite orbiting the Earth
Earth
directly above the equator, the plane of the satellite's orbit is the same as the Earth's equatorial plane, and the satellite's orbital inclination is 0°. The general case for a circular orbit is that it is tilted, spending half an orbit over the northern hemisphere and half over the southern
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US Air Force
Department of Defense Department of the Air ForceHeadquarters The Pentagon Arlington County, Virginia, U.S.Motto(s) "Aim High ... Fly-Fight-Win"[7] "Integrity first, Service before self, Excellence in all we do"[8]Colors Ultramarine
Ultramarine
blue, Golden yellow[9]          March The U.S. Air Force
U.S. Air Force
 Play (help·info)Anniversaries 18 SeptemberEngagementsSee listMexican Expedition (As Aviation Section, U.S. Signal Corps) World War I
World War I
(As Aviation Section, U.S. Signal Corps
Aviation Section, U.S

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Apsis
An apsis (Greek: ἁψίς; plural apsides /ˈæpsɪdiːz/, Greek: ἁψῖδες) is an extreme point in an object's orbit
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Medium Earth Orbit
Medium Earth
Earth
orbit (MEO), sometimes called intermediate circular orbit (ICO), is the region of space around the Earth
Earth
above low Earth
Earth
orbit (altitude of 2,000 km (1,243 mi)) and below geostationary orbit (altitude of 35,786 km (22,236 mi)).[1] The most common use for satellites in this region is for navigation, communication, and geodetic/space environment science.[1] The most common altitude is approximately 20,200 kilometres (12,552 mi)), which yields an orbital period of 12 hours, as used, for example, by the Global Positioning System
Global Positioning System
(GPS).[1] Other satellites in medium Earth
Earth
orbit include Glonass (with an altitude of 19,100 kilometres (11,868 mi))[citation needed] and Galileo (with an altitude of 23,222 kilometres (14,429 mi))[2] constellations
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Geocentric Orbit
A geocentric orbit or Earth
Earth
orbit involves any object orbiting Planet Earth, such as the Moon
Moon
or artificial satellites
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Cape Canaveral Air Force Station Space Launch Complex 17
Cape Canaveral Air Force Station Space Launch Complex 17[1][2] (SLC-17), previously designated Launch Complex 17 (LC-17), was a launch site at Cape Canaveral Air Force Station, Florida used for Thor and Delta rocket launches between 1958 and 2011. It was built in 1956 for use with the PGM-17 Thor missile, the first operational ballistic missile in the arsenal of the United States. More recently the launch complex has been used for vehicles in the Delta rocket family, derived from the Thor missile, to launch probes to the Moon and planets, solar observatories and weather satellites. SLC-17 features two expendable launch vehicle (ELV) launch pads, 17A and 17B. The pads were operated by the US Air Force's 45th Space Wing and have supported more than 300 Department of Defense, NASA and commercial missile and rocket launches
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Cape Canaveral Air Force Station
Cape Canaveral
Cape Canaveral
Air Force Station (CCAFS) (known as Cape Kennedy Air Force Station from 1963 to 1973) is an installation of the United States Air Force Space Command's 45th Space Wing.[2] CCAFS is headquartered at the nearby Patrick Air Force Base, and located on Cape Canaveral
Cape Canaveral
in Brevard County, Florida, CCAFS. The station is the primary launch head of America's Eastern Range[3] with three launch pads currently active (Space Launch Complexes 37B, 40, and 41). Popularly known as "Cape Kennedy" from 1963 to 1973, and as "Cape Canaveral" from 1949 to 1963 and from 1973 to the present, the facility is south-southeast of NASA's Kennedy Space Center
Kennedy Space Center
on adjacent Merritt Island, with the two linked by bridges and causeways
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Delta II
Delta II
Delta II
is an expendable launch system, originally designed and built by McDonnell Douglas. Delta II
Delta II
is part of the Delta rocket
Delta rocket
family and entered service in 1989. Delta II
Delta II
vehicles included the retired Delta 6000, and the two currently-used Delta 7000 variants ("Light" and "Heavy")
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