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AirLaunch Propane Engine
Air Launch LOx/Propane rocket engine. Flow calibration, ignition and initial short duration tests completed in 2005 of this upper stage rocket engine with application to future small spacecraft launchers.

Status: Developed 2005-. Date: 2005-. Thrust: 106.80 kN (24,010 lbf).

AirLaunch completed flow calibration, ignition and initial short duration tests of a liquid oxygen and propane powered upper stage rocket engine that has application for future small spacecraft launchers. The tests were conducted from April to June 2005 at the Civilian Flight Test Center, Mojave Spaceport. The engine employs an ablative chamber and nozzle, and was designed to produce 106,800 newtons force when operating in a vacuum with an extension nozzle. The extension was not installed for sea level tests. Testing demonstrated that the engine was stable, can be ignited quickly after shutdown and was ready to move into the next phase of development. Work on this engine was conducted in support of the DARPA/USAF FALCON program.



Country: USA. Propellants: Lox/C3H8. Agency: Air Launch. Bibliography: 4466.

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