USA-5
From Wikipedia, the free encyclopedia
| Names | Navstar 10 GPS I-10 GPS SVN-10 |
|---|---|
| Mission type | Navigation Technology |
| Operator | U.S. Air Force |
| COSPAR ID | 1984-097A |
| SATCAT no. | 15271 |
| Mission duration | 5 years (planned) 11 years (achieved) |
| Spacecraft properties | |
| Spacecraft | Navstar |
| Spacecraft type | GPS Block I |
| Manufacturer | Rockwell Space Systems |
| Launch mass | 758 kg (1,671 lb) |
| Dimensions | 5.3 meters of long |
| Power | 400 watts |
| Start of mission | |
| Launch date | 8 September 1984, 21:41:00 UTC |
| Rocket | Atlas E / SGS-2 (Atlas-14E) |
| Launch site | Vandenberg, SLC-3W |
| Contractor | Convair General Dynamics |
| Entered service | 3 October 1984 |
| End of mission | |
| Deactivated | 18 November 1995 |
| Orbital parameters | |
| Reference system | Geocentric orbit[1] |
| Regime | Medium Earth orbit (Semi-synchronous) |
| Perigee altitude | 19,962 km (12,404 mi) |
| Apogee altitude | 20,403 km (12,678 mi) |
| Inclination | 63.20° |
| Period | 718.00 minutes |
USA-5, also known as Navstar 10, GPS I-10 and GPS SVN-10, was an American navigation satellite launched in 1984 as part of the Global Positioning System (GPS) development programme. It was the tenth of eleven Block I GPS satellites to be launched.[2]
Global Positioning System (GPS) was developed by the U.S. Department of Defense (DoD) 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°. These vehicles are placed in 6 orbit planes with four operational satellites in each plane.[3]
Spacecraft
The first eleven spacecraft (GPS Block 1) were used to demonstrate the feasibility of the GPS system. They were 3-axis stabilized, nadir pointing using reaction wheels. Dual solar arrays supplied over 400 watts. They had S-band communications for control and telemetry and Ultra high frequency (UHF) cross-link between spacecraft. They were manufactured by Rockwell Space Systems, were 5.3 meters across with solar panels deployed, and had a design life expectancy of 5 years. Unlike the later operational satellites, GPS Block 1 spacecraft were inclined at 63°.[3]
