LR87-5
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. Used on Titan 2 launch vehicle. Engines refurbished for space launcher versions from decommissioned missiles between 1974-1982.
Configuration: twin fixed motors with individual turbo-pumped assemblies. First Flown: 1962 ICBM. Sept. 1988 orbital. Dry Mass: 739 kg. Length: 3.13 m. Maximum Diameter: 1.14 m. Engine Cycle: Gas generator. Propellants: hypergolic nitrogen tetroxide and Aerozine-50, delivered at 750 kg/sec. Mixture Ratio: 1.93:1. Thrust: 1913 kN sea level. Isp: 259 sec at sea level. Expansion Ratio: 8:1. Combustion Chamber Pressure: 53.3 atm. Burn Time: 158 sec.
Thrust (sl): 956.500 kN (215,030 lbf). Thrust (sl): 97,534 kgf. Engine: 739 kg (1,629 lb). Chamber Pressure: 54.00 bar. Area Ratio: 8. Thrust to Weight Ratio: 151.34. Oxidizer to Fuel Ratio: 1.93.
Related
- Family
- Storable liquid
- Country
- USA
- Launch Vehicles
- Titan II
- Propellants
- N2O4/Aerozine-50
- Agency
- Aerojet