| Names | Navstar 3 GPS I-3 GPS SVN-3 |
|---|---|
| Mission type | Navigation Technology |
| Operator | U.S. Air Force |
| COSPAR ID | 1978-093A [1] |
| SATCAT no. | 11054 |
| Mission duration | 5 years (planned) 13+1⁄2 years (achieved) |
| Spacecraft properties | |
| Spacecraft | Navstar |
| Spacecraft type | GPS Block I |
| Manufacturer | Rockwell Space Systems[2] |
| Launch mass | 758 kg (1,671 lb) |
| Dimensions | 5.3 meters of long |
| Power | 400 watts |
| Start of mission | |
| Launch date | 7 October 1978, 00:28:00 UTC |
| Rocket | Atlas F / SGS-1 (Atlas-47F) |
| Launch site | Vandenberg, SLC-3E |
| Contractor | Convair General Dynamics |
| Entered service | 13 November 1978 |
| End of mission | |
| Deactivated | 18 May 1992 |
| Orbital parameters | |
| Reference system | Geocentric orbit[3] |
| Regime | Medium Earth orbit (Semi-synchronous) |
| Perigee altitude | 20,285 km (12,605 mi) |
| Apogee altitude | 20,312 km (12,621 mi) |
| Inclination | 62.80° |
| Period | 722.60 minutes |
OPS 5113, also known as Navstar 3, GPS I-3 and GPS SVN-3, was an American navigation satellite launched in 1978 as part of the Global Positioning System development programme. It was the third of eleven Block I GPS satellites to be launched.[2]
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°. These vehicles are placed in 6 orbit planes with four operational satellites in each plane.[1]
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 m 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°.[1]
OPS 5113 was launched at 00:28 UTC on 7 October 1978, atop an Atlas F launch vehicle with an SGS-1 upper stage. The Atlas used had the serial number 47F, and was originally built as an Atlas F.[4] The launch took place from Space Launch Complex 3E at Vandenberg Air Force Base,[5] and placed OPS 5113 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-27 apogee motor.[2]
By 13 November 1978, OPS 5113 was in an orbit with a perigee of 20,285 km (12,605 mi), an apogee of 20,312 km (12,621 mi), a period of 722.60 minutes, and 62.80° of inclination to the equator.[6] The satellite had a design life of 5 years and a mass of 758 kg (1,671 lb).[2] It broadcast the PRN 06 signal in the GPS demonstration constellation, and was retired from service on 18 May 1992.
