Encyclopedia Astronautica
Astrorocket-2


N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 151,927/23,500 kg. Thrust 2,150.00 kN. Vacuum specific impulse 345 seconds. X-20 Dynasoar configuration. LR87-derivative engines.

Cost $ : 18.000 million.

Status: Study 1962.
Gross mass: 151,927 kg (334,941 lb).
Unfuelled mass: 23,500 kg (51,800 lb).
Height: 30.00 m (98.00 ft).
Diameter: 3.00 m (9.80 ft).
Span: 20.00 m (65.00 ft).
Thrust: 2,150.00 kN (483,330 lbf).
Specific impulse: 345 s.
Specific impulse sea level: 230 s.
Burn time: 181 s.

More... - Chronology...


Associated Countries
Associated Engines
  • LR87+ Aerojet N2O4/Aerozine-50 rocket engine. 1634.4 kN. Study 1965. Nominal improved LR87 in booster studies. Isp=293s. Used on Martin Astrorocket launch vehicle. More...

Associated Launch Vehicles
  • Martin Astrorocket American winged orbital launch vehicle. Early two-stage-to-orbit shuttle study, using storable propellants, Dynasoar-configuration delta wing orbiter and booster. More...

Associated Propellants
  • N2O4/Aerozine-50 Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Aerozine was a 50-50 mixture of hydrazine and UDMH developed for use in the Titan 2 missile. Copied in one Russian missile but otherwise straight UDMH used more commonly. Higher boiling point than UDMH. More...

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