Encyclopedia Astronautica

LR-87-3 Engine
Credit: Bob Fortune
Aerojet Lox/Kerosene rocket engine. 733.9 kN. Study 1957. Titan 1 booster engine. Surplus Flight Engines were available for various uses in the 1960's. Isp=290s. First flight 1959.

Thrust (sl): 647.900 kN (145,654 lbf). Thrust (sl): 66,067 kgf. Engine: 839 kg (1,849 lb). Chamber Pressure: 40.00 bar. Area Ratio: 8. Thrust to Weight Ratio: 89.204410011919. Oxidizer to Fuel Ratio: 1.91. Coefficient of Thrust vacuum: 1.84532204931916. Coefficient of Thrust sea level: 1.64532204931916.

Status: Study 1957.
Height: 3.13 m (10.26 ft).
Diameter: 1.53 m (5.00 ft).
Thrust: 733.90 kN (164,987 lbf).
Specific impulse: 290 s.
Specific impulse sea level: 256 s.
Burn time: 138 s.
Number: 140 .

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Associated Countries
See also
Associated Launch Vehicles
  • Super-Jupiter American orbital launch vehicle. The very first design that would lead to Saturn. A 1.5 million pound thrust booster using four E-1 engines - initial consideration of using a single USAF F-1 engine abandoned because of development time. Existing missile tankage was clustered above the engines. More...
  • Juno V-A American orbital launch vehicle. By 1958 the Super-Jupiter was called Juno V and the 4 E-1 engines were abandoned in favor of clustering 8 Jupiter IRBM engines below existing Redstone/Jupiter tankage. The A version had a Titan I ICBM as the upper stages. Masses, payload estimated. More...
  • Juno V-B American orbital launch vehicle. A proposed version of the Juno V for lunar and planetary missions used a Titan I ICBM first stage and a Centaur high-energy third stage atop the basic Juno V cluster. Masses, payload estimated. More...
  • Titan 1 American intercontinental ballistic missile. ICBM, built as back-up to Atlas, using two stages instead of one and a half, and conventional tank construction in lieu of balloon tanks. It was also to have been used for suborbital tests of the X-20A Dynasoar manned space plane. For unknown reasons never refurbished for use as space launcher and scrapped after being replaced by the Titan II in the missile role in mid-1960's. More...
  • Saturn A-1 American orbital launch vehicle. Projected first version of Saturn I, to be used if necessary before S-IV liquid hydrogen second stage became available. Titan 1 first stage used as second stage, Centaur third stage. Masses, payload estimated. More...

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

Associated Propellants
  • Lox/Kerosene Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. In January 1953 Rocketdyne commenced the REAP program to develop a number of improvements to the engines being developed for the Navaho and Atlas missiles. Among these was development of a special grade of kerosene suitable for rocket engines. Prior to that any number of rocket propellants derived from petroleum had been used. Goddard had begun with gasoline, and there were experimental engines powered by kerosene, diesel oil, paint thinner, or jet fuel kerosene JP-4 or JP-5. The wide variance in physical properties among fuels of the same class led to the identification of narrow-range petroleum fractions, embodied in 1954 in the standard US kerosene rocket fuel RP-1, covered by Military Specification MIL-R-25576. In Russia, similar specifications were developed for kerosene under the specifications T-1 and RG-1. The Russians also developed a compound of unknown formulation in the 1980's known as 'Sintin', or synthetic kerosene. More...

Associated Stages
  • Titan 1-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 76,203/4,000 kg. Thrust 1,467.91 kN. Vacuum specific impulse 290 seconds. More...

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