Encyclopedia Astronautica
LR87-7


Aerojet N2O4/Aerozine-50 rocket engine. 1086.1 kN. Study 1961. Version of LR-87-5 used on Gemini Titan 2 launch vehicle. Isp=296s. Proposed for unflown Titan 3L2, Titan 3L4 boosters. First flight 1962.

Thrust (sl): 946.700 kN (212,827 lbf). Thrust (sl): 96,535 kgf. Engine: 713 kg (1,571 lb). Chamber Pressure: 47.00 bar. Area Ratio: 9. Thrust to Weight Ratio: 155.333800841515. Oxidizer to Fuel Ratio: 1.9. Coefficient of Thrust vacuum: 2.2310677081288. Coefficient of Thrust sea level: 1.97574855919263.

Status: Study 1961.
Height: 3.13 m (10.26 ft).
Diameter: 1.53 m (5.00 ft).
Thrust: 1,086.10 kN (244,165 lbf).
Specific impulse: 296 s.
Specific impulse sea level: 258 s.
Burn time: 139 s.
Number: 212 .

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Associated Countries
See also
Associated Launch Vehicles
  • Titan 2 American intercontinental ballistic missile. ICBM, developed also as the launch vehicle for the manned Gemini spacecraft in the early 1960's. When the ICBM's were retired in the 1980's they were refurbished and a new series of launches began. More...
  • Titan 3L2 American orbital launch vehicle. Variant of Titan with 15 foot Large Diameter Core, 2 x 7 segment strap-ons. Man-rated, optimized for delivery of heavy payloads into LEO. Never developed. More...
  • Titan 3L4 American orbital launch vehicle. Variant of Titan with 15 foot Large Diameter Core, 4 x 7 segment strap-ons. Man rated, optimized for delivery of 40,000 pound manned payloads into 250 nm / 50 deg space station orbit. 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
  • Titan 2-1 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 117,866/6,736 kg. Thrust 2,172.23 kN. Vacuum specific impulse 296 seconds. More...
  • Titan LDC-1 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 350,000/20,000 kg. Thrust 4,344.46 kN. Vacuum specific impulse 296 seconds. 15 foot diameter core Titan proposed in 1960's for space station logistics. Masses estimated. More...

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