This page no longer updated from 31 October 2001. Latest version can be found at LR-91-7

Manufacturer Name: AJ23-135. Government Designation: LR-91-7. Designer: Aerojet. Used on stages: Titan 2-2, Titan LDC-2. Used on launch vehicles: Titan 2, Titan 3L2, Titan 3L4. Propellants: N2O4/Aerozine-50 Thrust(vac): 45,359 kgf. Thrust(vac): 444.80 kN. Isp: 316 sec. Isp (sea level): 160 sec. Burn time: 180 sec. Mass Engine: 565 kg. Diameter: 1.6 m. Chambers: 1. Chamber Pressure: 50.00 bar. Area Ratio: 45.00. Oxidizer to Fuel Ratio: 1.79. Thrust to Weight Ratio: 80.28. Country: USA. Status: Out of Production. First Flight: 1964. Last Flight: 1998. Flown: 19. Comments: Version used on Stage 2 of Gemini Launch Vehicle.
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Last update 12 March 2001.
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© Mark Wade, 2001 .