Encyclopedia Astronautica

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.
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 .

More... - Chronology...

Associated Countries
Associated Engines
  • 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...

Associated Propellants
  • 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...

Home - Browse - Contact
© / Conditions for Use