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SpaceDev Hybrid
SpaceDev N2O/Solid hybrid rocket engine. Rocketplane boost. Out of production. Used on Tier One launch vehicle. First flight 2002.

Status: Out of production. Date: 2001-2004. Number: 56 . Thrust: 73.50 kN (16,523 lbf). Gross mass: 2,700 kg (5,900 lb). Unfuelled mass: 300 kg (660 lb). Specific impulse: 250 s. Burn time: 90 s.

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 oxidizer, 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.

Chamber Pressure: 24.00 bar. Propellant Formulation: N2O/HTPB. Restarts: 4.



Family: Hybrid. Country: USA. Launch Vehicles: Tier One. Propellants: N2O/Solid. Stages: SpaceShip One. Agency: SpaceDev.

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