|
LR-91-5
|
|
Manufacturer Name: AJ23-133. Government Designation: LR91-5. Designer: Aerojet. Developed in: 1962. Application: Titan 2-2. Propellants: N2O4/Aerozine-50. Thrust(vac): 444.800 kN (99,995 lbf). Isp: 315 sec. Burn time: 175 sec. Mass Engine: 500 kg (1,100 lb). Diameter: 1.68 m (5.51 ft). Length: 2.80 m (9.10 ft). Chambers: 1. Chamber Pressure: 56.20 bar. Area Ratio: 49.20. Oxidizer to Fuel Ratio: 1.80. Thrust to Weight Ratio: 90.71. Country: USA. Status: Out of Production. First Flight: 1962. 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.
|
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.
© Mark Wade, 1997 - 2007 except where otherwise noted.
|
|
|
|