SpaceDev Hybrid

Designer: SpaceDev. Developed in: 2001-2004. Application: Rocketplane boost. Gross Mass: 2,700 kg (5,900 lb). Empty Mass: 300 kg (660 lb). Propellants: N2O/Solid. Thrust(vac): 73.500 kN (16,523 lbf). Isp: 250 sec. Burn time: 90 sec. Chambers: 1. Chamber Pressure: 24.00 bar. Country: USA. Status: Out of production. First Flight: 2002. Last Flight: 2004. Flown: 56.

Hybrid motor selected for SpaceFlightOne after competitive testing with an eEc design. In September 2003, Scaled Composites announced that it had selected SpaceDev for propulsion support for its SpaceShipOne project. In a series of flights in late 2004, SpaceDev's hybrid rocket motor powered SpaceShipOne to suborbital space twice in two weeks, thus propelling it to win the Ansari X Prize. Nitrous oxide oxidiser, proprietary HTPB solid fuel. SpaceDev built the casing, but the 25:1 expansion nozzle was fabricated by AEA. All data is estimated; actual figures are considered proprietary.

SpaceDev Hybrid used on Rocket Stages

Used on stage: SpaceShipOne. on launch vehicle: Tier One.

SpaceDev Hybrid used on Spacecraft

Used on: SpaceShipOne.

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