|Operator||U.S. Air Force|
|COSPAR ID||1992-019A |
|Mission duration||7.5 years (planned)|
5.33 years (Achieved)
|Spacecraft type||GPS Block IIA |
|Launch mass||840 kg (1,850 lb)|
|Dimensions||5.3 m (17 ft) of long|
|Start of mission|
|Launch date||10 April 1992, 03:20:00 UTC|
|Rocket||Delta II 7925-9.5|
|Launch site||Cape Canaveral, LC-17B|
|Entered service||10 April 1992|
|End of mission|
|Deactivated||15 August 1997|
|Reference system||Geocentric orbit|
|Regime||Medium Earth orbit|
|Slot||C2 (slot 2 plane C)|
|Perigee altitude||19,877 km (12,351 mi)|
|Apogee altitude||20,390 km (12,670 mi)|
USA-80, also known as GPS IIA-4, GPS II-13 and GPS SVN-28, was an American navigation satellite which formed part of the Global Positioning System. It was the fourth 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 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.
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.
USA-80 was launched at 03:20:00 UTC on 10 April 1992, atop a Delta II carrier rocket, flight number D208, flying in the 7925-9.5 configuration. The launch took place from Launch Complex 17B (LC-17B) at the Cape Canaveral Air Force Station (CCAFS), and placed USA-80 into a transfer orbit. 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 19,877 km (12,351 mi), an apogee of 20,390 km (12,670 mi), a period of 716.00 minutes, and 55.10° 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 840 kg (1,850 lb). It had a design life of 7.5 years; however, it was retired early, on 15 August 1997. It was replaced by USA-117.