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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)
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