USA-100

Summary

USA-100
NamesNavstar 2A-15
GPS IIA-15
GPS II-24
GPS SVN-36
Mission typeNavigation
OperatorU.S. Air Force
COSPAR ID1994-016A [1]
SATCAT no.23027
Mission duration7.5 years (planned)
20 years (achieved)
Spacecraft properties
SpacecraftGPS IIA
Spacecraft typeGPS Block IIA [2]
ManufacturerRockwell International
Launch mass840 kg (1,850 lb)
Dimensions5.3 m (17 ft) of long
Power710 watts
Start of mission
Launch date10 March 1994, 03:40:01 UTC
RocketDelta II 7925-9.5
(Delta D226)
Launch siteCape Canaveral, LC-17A
ContractorMcDonnell Douglas
Entered service15 April 1994
End of mission
DisposalGraveyard orbit
Deactivated21 February 2014
Orbital parameters
Reference systemGeocentric orbit [3]
RegimeMedium Earth orbit
(Semi-synchronous)
SlotC1 (slot 1 plane C)
Perigee altitude19,986 km (12,419 mi)
Apogee altitude20,315 km (12,623 mi)
Inclination54.9°
Period716.69 minutes
← USA-96 (GPS IIA-14)
USA-117 (GPS IIA-16) →
 

USA-100, also known as GPS IIA-15, GPS II-24 and GPS SVN-36, is an American navigation satellite which forms part of the Global Positioning System. It was the fifteenth of nineteen Block IIA GPS satellites to be launched.

Background

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 55.0°. These vehicles are placed in 6 orbit planes with four operational satellites in each plane.[1]

GPS Block 2 was the operational system, following the demonstration system composed of Block 1 (Navstar 1 - 11) spacecraft. These spacecraft were 3-axis stabilized, nadir pointing using reaction wheels. Dual solar arrays supplied 710 watts of power. They used S-band (SGLS) communications for control and telemetry and Ultra high frequency (UHF) cross-link between spacecraft. The payload consisted of two L-band navigation signals at 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft carried 2 rubidium and 2 Cesium clocks and nuclear detonation detection sensors. Built by Rockwell Space Systems for the U.S. Air force, the spacecraft measured 5.3 m across with solar panels deployed and had a design life of 7.5 years.[1]

Launch

USA-100 was launched at 03:40:01 UTC on 10 March 1994, atop a Delta II launch vehicle, flight number D226, flying in the 7925-9.5 configuration.[4] The launch took place from Launch Complex 17A (LC-17A) at the Cape Canaveral Air Force Station (CCAFS),[5] and placed USA-100 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor.[2]

Mission

On 15 April 1994, USA-100 was in an orbit with a perigee of 19,986 km (12,419 mi), an apogee of 20,315 km (12,623 mi), a period of 716.69 minutes, and 54.9° of inclination to the equator.[3] It broadcasts the PRN 06 signal, and operates in slot 1 of plane C of the GPS constellation.[6] The satellite has a mass of 840 kg (1,850 lb). It had a design life of 7.5 years,[2] but it remained in service until 21 February 2014, shortly after the launch of USA-248.

References

  1. ^ a b c "Display: Navstar 2A-15 1994-016A". NASA. 14 May 2020. Retrieved 20 December 2020. This article incorporates text from this source, which is in the public domain.
  2. ^ a b c Krebs, Gunter. "GPS-2A (Navstar-2A)". Gunter's Space Page. Retrieved 10 July 2012.
  3. ^ a b McDowell, Jonathan. "Satellite Catalog". Jonathan's Space Report. Retrieved 11 July 2012.
  4. ^ McDowell, Jonathan. "Launch Log". Jonathan's Space Report. Retrieved 11 July 2012.
  5. ^ McDowell, Jonathan. "Launch List". Launch Vehicle Database. Jonathan's Space Report. Retrieved 11 July 2012.
  6. ^ Wade, Mark. "Navstar". Encyclopedia Astronautica. Retrieved 10 July 2012.