Encyclopedia Astronautica

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.

Thrust (sl): 1,439.200 kN (323,545 lbf). Thrust (sl): 146,757 kgf.

Status: Study 1965.
Thrust: 1,634.40 kN (367,428 lbf).
Specific impulse: 293 s.
Specific impulse sea level: 258 s.
Burn time: 164 s.

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Associated Countries
See also
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 Manufacturers and Agencies
  • Aerojet American manufacturer of rockets, spacecraft, and rocket engines. Aerojet, Sacramento, CA, USA. 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...

Associated Stages
  • Astrorocket-1 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. More...
  • 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. More...

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