This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Manufacturer Name: AJ23-133. Government Designation: LR-91-5. Designer: Aerojet. Developed in: 1962. Application: Titan 2-2. Used on launch vehicles: Titan 2. Propellants: N2O4/Aerozine-50 Thrust(vac): 45,357 kgf. Thrust(vac): 444.80 kN. Isp: 315 sec. Burn time: 175 sec. Mass Engine: 500 kg. Diameter: 1.7 m. Length: 2.8 m. Chambers: 1. Chamber Pressure: 56.20 bar. Area Ratio: 49.20. Oxidizer to Fuel Ratio: 1.80. Country: USA. Status: Out of Production. Comments: Titan 2 ICBM Stage 2. Configuration: scaled down version of stage 1 engine featuring fixed single chamber. Applications: Titan 2 stage 2. Engine Cycle: gas generator. Propellant flow rate: 163 kg/sec. Mixture Ratio: 1.80.
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Last update 12 March 2001.
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