LR-91-11

Manufacturer Name: AJ23-140. Government Designation: LR91-11. Designer: Aerojet. Propellants: N2O4/Aerozine-50. Thrust(vac): 467.000 kN (104,985 lbf). Thrust(sl): 232.700 kN (52,313 lbf). Isp: 316 sec. Isp (sea level): 160 sec. Burn time: 247 sec. Mass Engine: 589 kg (1,298 lb). Diameter: 1.63 m (5.34 ft). Length: 2.81 m (9.21 ft). Chambers: 1. Chamber Pressure: 59.30 bar. Area Ratio: 49.20. Oxidizer to Fuel Ratio: 1.86. Thrust to Weight Ratio: 80.85. Country: USA. Status: Out of production. First Flight: 1968. Last Flight: 2005. Flown: 267.

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.

LR-91-11 used on Rocket Stages

Used on stage: Titan 3A-2. on launch vehicle: Titan 3A.

Used on stage: Titan 3A-2. on launch vehicle: Titan 3B.

Used on stage: Titan 3A-2. on launch vehicle: Titan 3C.

Used on stage: Titan 3A-2. on launch vehicle: Titan 3C7.

Used on stage: Titan 3A-2. on launch vehicle: Titan 3D.

Used on stage: Titan 3A-2. on launch vehicle: Titan 3E.

Used on stage: Titan 3B-2. on launch vehicle: Titan 34D.

Used on stage: Titan 3B-2. on launch vehicle: Titan 3B.

Used on stage: Titan 3B-2. on launch vehicle: Titan 3BAS2.

Used on stage: Titan 3B-2. on launch vehicle: Titan 3M.

Used on stage: Titan 4-2. on launch vehicle: Titan 4.

Used on stage: Titan 4-2. on launch vehicle: Titan 4B.

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