USA-84
| Mission type | Navigation |
|---|---|
| Operator | US Air Force |
| COSPAR ID | 1992-058A[1] |
| SATCAT № | 22108[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 | 9 September 1992, 08:57:00 UTC |
| Rocket | Delta II 7925-9.5, D214[3] |
| Launch site | Cape Canaveral LC-17A[3] |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Medium Earth (Semi-synchronous) |
| Perigee | 19,914 kilometres (12,374 mi)[4] |
| Apogee | 20,451 kilometres (12,708 mi)[4] |
| Inclination | 54.7 degrees[4] |
| Period | 717.98 minutes[4] |
USA-84, also known as GPS IIA-6, GPS II-15 and GPS SVN-27, is an American navigation satellite which forms part of the Global Positioning System. It was the sixth of nineteen Block IIA GPS satellites to be launched.
USA-84 was launched at 08:57:00 UTC on 9 September 1992, atop a Delta II carrier rocket, flight number D214, flying in the 7925-9.5 configuration.[3] The launch took place from Launch Complex 17A at the Cape Canaveral Air Force Station,[5] and placed USA-84 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor.[2]
On 11 October 1992, USA-84 was in an orbit with a perigee of 19,914 kilometres (12,374 mi), an apogee of 20,451 kilometres (12,708 mi), a period of 717.98 minutes, and 54.7 degrees of inclination to the equator.[4] It had PRN 27, and operated in slot 4 of plane A of the GPS constellation.[6] The satellite has a mass of 1,816 kilograms (4,004 lb). It had a design life of 7.5 years,[2] but was in service for twenty years, until its retirement in October 2012.
References
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