USA-80

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USA-80
NamesNavstar 2A-04
GPS IIA-4
GPS II-13
GPS SVN-28
Mission type Navigation
Operator U.S. Air Force
COSPAR ID 1992-019A [1]
SATCAT no. 21930
Mission duration7.5 years (planned)
5.33 years (Achieved)
Spacecraft properties
Spacecraft GPS IIA
Spacecraft type GPS Block IIA [2]
Manufacturer Rockwell International
Launch mass840 kg (1,850 lb)
Dimensions5.3 m (17 ft) of long
Power710 kg
Start of mission
Launch date10 April 1992, 03:20:00 UTC
Rocket Delta II 7925-9.5
(Delta D208)
Launch site Cape Canaveral, LC-17B
Contractor McDonnell Douglas
Entered service10 April 1992
End of mission
Disposal Graveyard orbit
Deactivated15 August 1997
Orbital parameters
Reference system Geocentric orbit
Regime Medium Earth orbit
(Semi-synchronous)
SlotC2 (slot 2 plane C)
Perigee altitude 19,877 km (12,351 mi)
Apogee altitude 20,390 km (12,670 mi)
Inclination 55.10°
Period 716.00 minutes
←  USA-79 (GPS IIA-3)
USA-83 (GPS IIA-5) →
 

USA-80, also known as GPS IIA-4, GPS II-13 and GPS SVN-28, was an American navigation satellite which formed part of the Global Positioning System. It was the fourth of nineteen Block IIA GPS satellites to be launched.

Contents

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-80 was launched at 03:20:00 UTC on 10 April 1992, atop a Delta II carrier rocket, flight number D208, flying in the 7925-9.5 configuration. [3] The launch took place from Launch Complex 17B (LC-17B) at the Cape Canaveral Air Force Station (CCAFS), [4] and placed USA-80 into a transfer orbit. The satellite raised itself into medium Earth orbit using a Star-37XFP apogee motor. [2]

Mission

On 12 May 1992, USA-80 was in an orbit with a perigee of 19,877 km (12,351 mi), an apogee of 20,390 km (12,670 mi), a period of 716.00 minutes, and 55.10° of inclination to the equator. [5] It had PRN 28, and operated in slot 2 of plane C of the GPS constellation. The satellite had a mass of 840 kg (1,850 lb). It had a design life of 7.5 years; [2] however, it was retired early, on 15 August 1997. It was replaced by USA-117.

Related Research Articles

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References

  1. 1 2 3 "Display: Navstar 2A-04 1992-019A". NASA. 14 May 2020. Retrieved 18 December 2020.PD-icon.svg This article incorporates text from this source, which is in the public domain .
  2. 1 2 3 Krebs, Gunter. "GPS-2A (Navstar-2A)". Gunter's Space Page. Retrieved 10 July 2012.
  3. ↑ McDowell, Jonathan. "Launch Log". Jonathan's Space Report. Retrieved 10 July 2012.
  4. ↑ McDowell, Jonathan. "Launch List". Launch Vehicle Database. Jonathan's Space Report. Retrieved 10 July 2012.
  5. ↑ "Trajectory: Navstar 2A-04 1992-019A". NASA. 14 May 2020. Retrieved 18 December 2020.PD-icon.svg This article incorporates text from this source, which is in the public domain .
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