USA-80
| Mission type | Navigation |
|---|---|
| Operator | US Air Force |
| COSPAR ID | 1992-019A[1] |
| SATCAT № | 21930[1] |
| Mission duration | 7.5 years (planned)[2] |
| Spacecraft properties | |
| Spacecraft type | GPS Block IIA[2] |
| Manufacturer | Rockwell[2] |
| Launch mass | 1,816 kilograms (4,004 lb)[2] |
| Start of mission | |
| Launch date | 10 April 1992, 03:20:00 UTC |
| Rocket | Delta II 7925-9.5, D208[3] |
| Launch site | Cape Canaveral LC-17B[3] |
| End of mission | |
| Deactivated | 15 August 1997 |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Medium Earth (Semi-synchronous) |
| Perigee | 19,979 kilometres (12,414 mi)[4] |
| Apogee | 20,384 kilometres (12,666 mi)[4] |
| Inclination | 55.1 degrees[4] |
| Period | 717.94 minutes[4] |
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.
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.[3] The launch took place from Launch Complex 17B at the Cape Canaveral Air Force Station,[5] and placed USA-80 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor.[2]
On 12 May 1992, USA-80 was in an orbit with a perigee of 19,979 kilometres (12,414 mi), an apogee of 20,384 kilometres (12,666 mi), a period of 717.94 minutes, and 55.1 degrees of inclination to the equator.[4] It had PRN 28, and operated in slot 2 of plane C of the GPS constellation. The satellite had a mass of 1,816 kilograms (4,004 lb). It had a design life of 7.5 years;[2] however, it was retired early, on 15 August 1997. It was replaced by USA-117.
References
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- ↑ 2.0 2.1 2.2 2.3 2.4 2.5 Lua error in package.lua at line 80: module 'strict' not found.
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- ↑ 4.0 4.1 4.2 4.3 4.4 Lua error in package.lua at line 80: module 'strict' not found.
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