USA-35
| Mission type | Navigation |
|---|---|
| Operator | US Air Force |
| COSPAR ID | 1989-013A |
| SATCAT № | 19802 |
| Mission duration | 7.5 years (planned)[1] |
| Spacecraft properties | |
| Spacecraft type | GPS Block II[1] |
| Manufacturer | Rockwell[1] |
| Launch mass | 840 kilograms (1,850 lb)[2] |
| Start of mission | |
| Launch date | 14 February 1989, 18:30 UTC |
| Rocket | Delta II 6925,[3] D184[3] |
| Launch site | Cape Canaveral LC-17A[3] |
| End of mission | |
| Deactivated | 26 March 2000 |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Medium Earth (Semi-synchronous) |
| Perigee | 19,858 kilometres (12,339 mi)[4] |
| Apogee | 20,270 kilometres (12,600 mi)[4] |
| Inclination | 55.1 degrees[4] |
| Period | 713.2 minutes[4] |
USA-35, also known as GPS II-1 and GPS SVN-14, was an American navigation satellite which formed part of the Global Positioning System. It was the first of nine Block II GPS satellites to be launched, which were the first operational GPS satellites to be launched.
USA-35 was launched at 18:30 UTC on 14 February 1989, atop a Delta II carrier rocket, flight number D184, flying in the 6925 configuration.[3] This was the maiden flight of the Delta II. The launch took place from Launch Complex 17A at the Cape Canaveral Air Force Station,[5] and placed USA-35 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor.[1]
On 16 March 1989, USA-35 was in an orbit with a perigee of 19,858 kilometres (12,339 mi), an apogee of 20,270 kilometres (12,600 mi), a period of 713.2 minutes, and 55.1 degrees of inclination to the equator.[4] The satellite had a mass of 840 kilograms (1,850 lb), and generated 710 watts of power.[2] It had a design life of 7.5 years;[1] however, it operated until 26 March 2000, when its reaction wheels failed. It was decommissioned on 14 April 2000, having been replaced by USA-150.[6]
References
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