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Falcon SLV-2
Michoud hybrid rocket LOx/Solid engine. Upper stages. Study 2005. Part of the USAF FALCON program to assess hybrid propulsion applications for a responsive small launch vehicle.

Status: Study 2005. Thrust: 133.00 kN (29,899 lbf).

In November 2003, Lockheed Martin-Michoud Operations was awarded a six-month study contract from DARPA as part of the USAF FALCON program to assess hybrid propulsion applications for a responsive small launch vehicle. This study concluded in May 2004. In September 2004, FALCON competitors began a 10-month design phase to be followed by a down-select to possibly two competitors, and a winning design to be selected in 2007. Lockheed Martin-Michoud's all-hybrid two-stage vehicle would deliver a payload up to 455 kilograms to LEO and, if selected, would establish hybrid propulsion as a viable space launch booster technology. The second stage would require approximately 133,333 newtons of thrust to meet mission objectives using a HTPB and LOX motor.

Propellant Formulation: Lox/HTPB.



Family: Hybrid. Country: USA. Propellants: Lox/Solid. Agency: Michoud.

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