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Pegasus XL

Background Information
First Launch:
June 1994
Flight Rate:
Six per year (advertised Pegasus capability)
Launch Site:
Carried by L-1011 out of CCAS, VAFB, or EAFB (USA)
Capability:
600 lb to 250 NM polar orbit

History

  • Pegasus 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
  • XL version is stretched derivative

Description

  • Three-stage* winged vehicle, air launched from L-1011 carrier aircraft
  • Stage 1 Alliant Techsystems solid rocket motor, generating 160,700 lb of thrust
  • Stage 2 solid rocket motor, generating 44,300 lb of thrust
  • Stage 3 solid rocket motor, generating 8,600 lb of thrust

Profile

Length:
55.4 ft
Launch Weight:
50,000 lb
Diameter
4.2 ft
Liftoff Thrust:
160,700 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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