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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)
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