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Pegasus

Background Information
First Launch:
April 1990
Flight Rate:
Six per year (advertised capability)
Launch Site:
Carried by L-1011 out of CCAS, VAFB, or EAFB (USA)
Capability:
620 lb to 100 NM polar orbit

History

  • Development program began in 1987
  • July 1988, DARPA contracted for one satellite launch with options for five more launches
  • April 1991, selected for Air Force small launch vehicle

Description

  • Three-stage* winged vehicle, air launched from L-1011 carrier aircraft
  • Hybrid standard version with modifications for launch from L-1011 aircraft (standard version formerly launched from B-52 aircraft)
  • Stage 1 Alliant Techsystems solid rocket motor, generating 109,400 lb of thrust
  • Stage 2 solid rocket motor, generating 27,600 lb of thrust
  • Stage 3 solid rocket motor, generating 7,800 lb of thrust

Profile

Length:
50.9 ft
Launch Weight:
41,500 lb
Diameter
4.2 ft
Liftoff Thrust:
109,400 lb
Payload Fairing:
6.3 ft x 3.8 ft

* Optional fourth stage available -- Hydrazine Auxiliary Propulsion System (HAPS)

Other Resources


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