This page no longer updated from 31 October 2001. Latest version can be found at LR-91-11

Manufacturer Name: AJ23-140. Government Designation: LR-91-11. Designer: Aerojet. Used on stages: Titan 3A-2, Titan 3B-2, Titan 4-2. Used on launch vehicles: Titan 34B, Titan 34D, Titan 3A, Titan 3B, Titan 3BAS2, Titan 3C, Titan 3C7, Titan 3D, Titan 3E, Titan 3M, Titan 4, Titan 4B. Propellants: N2O4/Aerozine-50 Thrust(vac): 46,857 kgf. Thrust(vac): 467.00 kN. Isp: 316 sec. Isp (sea level): 160 sec. Burn time: 247 sec. Mass Engine: 589 kg. Diameter: 1.6 m. Length: 2.8 m. Chambers: 1. Chamber Pressure: 58.50 bar. Area Ratio: 49.20. Oxidizer to Fuel Ratio: 1.86. Thrust to Weight Ratio: 80.85. Country: USA. Status: In Production. First Flight: 1964. Last Flight: 1999. Flown: 185.

First Flown: late 1968 Titan 3, 1989 Titan 4. Dry Mass: 589 kg. Length: 281 cm. Maximum Diameter: 163 cm (skirt outer diameter). Mounting: fixed, but turbine exhaust utilized for roll control. Engine Cycle: gas generator. Oxidizer: nitrogen tetroxide at 97 kg/sec. Fuel: Aerozine-50 at 54.7 kg/sec. Mixture Ratio: 1.86:1. Thrust: 467 kN vacuum. Isp: 316 sec vacuum. Expansion Ratio: 49.2:1. Combustion Chamber Pressure: 58.5 atm. Cooling Method: fuel regenerative thrust chamber, with separate ablative skirt. Burn Time: 247 secs.Used in Titan 4-2; Titan 3B-2; Titan 3A-2.

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Last update 12 March 2001.
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