N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 981,859/132,000 kg. Thrust 14,700.00 kN. Vacuum specific impulse 293 seconds. Delta wing configuration. LR87-derivative engines.
Cost $ : 18.000 million. No Engines: 9.
Status: Study 1962.
More... - Chronology...
Gross mass: 981,859 kg (2,164,628 lb).
Unfuelled mass: 132,000 kg (291,000 lb).
Height: 65.00 m (213.00 ft).
Diameter: 7.00 m (22.90 ft).
Span: 40.00 m (131.00 ft).
Thrust: 14,700.00 kN (3,304,600 lbf).
Specific impulse: 293 s.
Specific impulse sea level: 258 s.
Burn time: 164 s.
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...
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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