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LR-87-5
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Manufacturer Name: AJ23-132. Government Designation: LR87-5. Designer: Aerojet. Propellants: N2O4/Aerozine-50. Thrust(vac): 1,096.800 kN (246,570 lbf). Thrust(sl): 956.500 kN (215,030 lbf). Isp: 297 sec. Isp (sea level): 259 sec. Burn time: 155 sec. Mass Engine: 739 kg (1,629 lb). Diameter: 1.14 m (3.74 ft). Length: 3.13 m (10.26 ft). Chambers: 1. Chamber Pressure: 54.00 bar. Area Ratio: 8.00. Oxidizer to Fuel Ratio: 1.93. Thrust to Weight Ratio: 151.34. Country: USA. Status: Out of Production. First Flight: 1974. Last Flight: 1982. Engines refurbished for space launcher versions from decommissioned missiles between 1974 - 1982.. Configuration: twin fixed motors with individual turbo-pumped assemblies. Application: Titan 2 Stage 1. First Flown: 1962 ICBM. Sept. 1988 orbital. Dry Mass: 739 kg. Length: 3.13 m. Maximum Diameter: 1.14 m. Engine Cycle: Gas generator. Propellants: hypergolic nitrogen tetroxide and Aerozine-50, delivered at 750 kg/sec. Mixture Ratio: 1.93:1. Thrust: 1913 kN sea level. Isp: 259 sec at sea level. Expansion Ratio: 8:1. Combustion Chamber Pressure: 53.3 atm. Burn Time: 158 sec.
Bibliography and Further Reading - Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...
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