USA-80
| Names | Navstar 2A-04 GPS IIA-4 GPS II-13 GPS SVN-28 |
|---|---|
| Mission type | Navigation |
| Operator | U.S. Air Force |
| COSPAR ID | 1992-019A[1] |
| SATCATno. | 21930 |
| Mission duration | 7.5 years (planned) 5.33 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 kg |
| Start of mission | |
| Launch date | 10 April 1992, 03:20:00UTC |
| Rocket | Delta II7925-9.5 (Delta D208) |
| Launch site | Cape Canaveral,LC-17B |
| Contractor | McDonnell Douglas |
| Entered service | 10 April 1992 |
| End of mission | |
| Disposal | Graveyard orbit |
| Deactivated | 15 August 1997 |
| Orbital parameters | |
| Reference system | Geocentric orbit |
| Regime | Medium Earth orbit (Semi-synchronous) |
| Slot | C2 (slot 2 plane C) |
| Perigee altitude | 19,877 km (12,351 mi) |
| Apogee altitude | 20,390 km (12,670 mi) |
| Inclination | 55.10° |
| Period | 716.00 minutes |
USA-80,also known asGPS IIA-4,GPS II-13andGPS SVN-28,was an Americannavigation satellitewhich formed part of theGlobal Positioning System.It was the fourth of nineteenBlock IIAGPS satellites to be launched.
Background
[edit]Global Positioning System (GPS) was developed by theU.S. Department of Defenseto provide all-weather round-the-clock navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral asset in numerous civilian applications and industries around the globe, including recreational used (e.g., boating, aircraft, hiking), corporate vehicle fleet tracking, and surveying. 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 were3-axis stabilized,nadirpointing usingreaction wheels.Dual solar arrays supplied 710 watts of power. They usedS-band(SGLS) communications for control and telemetry andUltra high frequency(UHF) cross-link between spacecraft. The payload consisted of twoL-bandnavigation signals at 1575.42MHz(L1) and 1227.60 MHz (L2). Each spacecraft carried 2rubidiumand 2Cesiumclocks and nuclear detonation detection sensors. Built byRockwell Space Systemsfor 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]
Launch
[edit]USA-80 was launched at 03:20:00 UTC on 10 April 1992, atop aDelta IIcarrier rocket, flight number D208, flying in the 7925-9.5 configuration.[3]The launch took place fromLaunch Complex 17B(LC-17B) at theCape Canaveral Air Force Station(CCAFS),[4]and placed USA-80 into a transfer orbit. The satellite raised itself intomedium Earth orbitusing aStar-37XFPapogee motor.[2]
Mission
[edit]On 12 May 1992, USA-80 was in an orbit with aperigeeof 19,877 km (12,351 mi), anapogeeof 20,390 km (12,670 mi), aperiodof 716.00 minutes, and 55.10° ofinclinationto theequator.[5]It had PRN 28, and operated in slot 2 of plane C of the GPS constellation. The satellite had a mass of 840 kg (1,850 lb). It had a design life of 7.5 years;[2]however, it was retired early, on 15 August 1997. It was replaced byUSA-117.
References
[edit]
- ^abc"Display: Navstar 2A-04 1992-019A".NASA. 14 May 2020.Retrieved18 December2020.
This article incorporates text from this source, which is in thepublic domain.
- ^abcKrebs, Gunter."GPS-2A (Navstar-2A)".Gunter's Space Page.Retrieved10 July2012.
- ^McDowell, Jonathan."Launch Log".Jonathan's Space Report.Retrieved10 July2012.
- ^McDowell, Jonathan."Launch List".Launch Vehicle Database.Jonathan's Space Report. Archived fromthe originalon 15 August 2020.Retrieved10 July2012.
- ^"Trajectory: Navstar 2A-04 1992-019A".NASA. 14 May 2020.Retrieved18 December2020.This article incorporates text from this source, which is in thepublic domain.