LR91-11
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Aerojet N2O4/Aerozine-50 rocket engine. Out of production. Second stage engine for Titan 3 and 4. First flight 1968.
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.
Thrust (sl): 232.700 kN (52,313 lbf). Thrust (sl): 23,725 kgf. Engine: 589 kg (1,298 lb). Chamber Pressure: 59.30 bar. Area Ratio: 49.2. Thrust to Weight Ratio: 80.8501649339037. Oxidizer to Fuel Ratio: 1.86. Coefficient of Thrust vacuum: 1.85833549524615. Coefficient of Thrust sea level: 1.01730985422051.
Related
- Family
- Storable liquid
- Country
- USA
- Launch Vehicles
- Titan IIIC, Titan 3BAS2, Titan IIIA, Titan 3M, Titan 3C7, Titan IIIB, Titan IIID, Titan IIIE, Titan 34B, Titan 34D, Titan 4, Titan 4B
- Propellants
- N2O4/Aerozine-50
- Stages
- Titan 3A-2, Titan 3B-2, Titan 4-2
- Agency
- Aerojet