N2O/Solid propellant rocket stage. Loaded/empty mass 3,600/1,200 kg. Thrust 73.50 kN. Vacuum specific impulse 250 seconds. Wing area 15 sq m.
Propellant Formulation: N2O/HTPB.
Status: Retired 2004.
More... - Chronology...
Gross mass: 3,600 kg (7,900 lb).
Unfuelled mass: 1,200 kg (2,600 lb).
Diameter: 1.52 m (4.98 ft).
Span: 5.00 m (16.40 ft).
Thrust: 73.50 kN (16,523 lbf).
Specific impulse: 250 s.
Burn time: 80 s.
Number: 56 .
SpaceDev Hybrid SpaceDev N2O/Solid hybrid rocket engine. 73.5 kN. Rocketplane boost. Out of production. Isp=250s. Used on Tier One launch vehicle. First flight 2002. More...
Associated Launch Vehicles
Tier One American winged rocketplane. Burt Rutan's Tier One was the second manned reusable suborbital launch system (after the B-52/X-15). But it was developed privately at a small fraction of the cost. More...
N2O/Solid Liquid nitrous oxide (N2O / dinitrogen monoxide / 'laughing gas') is the oxidiser of choice for hybrid rocket motors because it is benign, storable, and self-pressurising to 48 atmospheres at 17 deg C. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...
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