USA-91
From Wikipedia, the free encyclopedia
| Names | Navstar 2A-11 GPS IIA-11 GPS II-20 GPS SVN-37 |
|---|---|
| Mission type | Navigation |
| Operator | U.S. Air Force |
| COSPAR ID | 1993-032A[1] |
| SATCAT no. | 22657 |
| Mission duration | 7.5 years (planned) 14.5 years (achieved) |
| Spacecraft properties | |
| Spacecraft | GPS IIA |
| Spacecraft type | GPS Block IIA[2] |
| Manufacturer | Rockwell International |
| Launch mass | 840 kg (1,850 lb) |
| Dimensions | 5.3 m (17 ft) of long |
| Power | 710 watts |
| Start of mission | |
| Launch date | 13 May 1993, 00:07:00 UTC |
| Rocket | Delta II 7925-9.5 (Delta D220) |
| Launch site | Cape Canaveral, LC-17A |
| Contractor | McDonnell Douglas |
| Entered service | 14 June 1993 |
| End of mission | |
| Disposal | Graveyard orbit |
| Deactivated | 18 March 2016 |
| Last contact | 20 December 2007 |
| Orbital parameters | |
| Reference system | Geocentric orbit[3] |
| Regime | Medium Earth orbit (Semi-synchronous) |
| Slot | C4 (slot 4 plane C) |
| Perigee altitude | 20,033 km (12,448 mi) |
| Apogee altitude | 20,334 km (12,635 mi) |
| Inclination | 54.9° |
| Period | 717.88 minutes |
USA-91, also known as GPS IIA-11, GPS II-20 and GPS SVN-37, was an American navigation satellite which formed part of the Global Positioning System. It was the eleventh of nineteen Block IIA GPS satellites to be launched.
Global Positioning System (GPS) was developed by the U.S. Department of Defense to provide all-weather round-the-clock navigation capabilities for military ground, sea, and air forces. Since its introduction, GPS has also developed into a valuable tool for a wide range of civilian uses and sectors, including surveying, tracking corporate vehicle fleets, and outdoor enjoyment (such as sailing, flying, and hiking). GPS employs 24 spacecraft in 20,200 km circular orbits inclined at 55.0°. These vehicles are placed in 6 orbit planes with four operational satellites in each plane.[1]
GPS Block 2 was the operational system, following the demonstration system composed of Block 1 (Navstar 1 - 11) spacecraft. These spacecraft were 3-axis stabilized, nadir pointing using reaction wheels. Dual solar arrays supplied 710 watts of power. They used S-band (SGLS) communications for control and telemetry and Ultra high frequency (UHF) cross-link between spacecraft. The payload consisted of two L-band navigation signals at 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft carried 2 rubidium and 2 Cesium clocks and nuclear detonation detection sensors. Built by Rockwell Space Systems for the U.S. Air force, the spacecraft measured 5.3 m across with solar panels deployed and had a design life of 7.5 years.[1]
