LR105-7
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Credit: Boeing / Rocketdyne
Rocketdyne LOx/Kerosene rocket engine. Atlas space launchers. Out of production. Atlas Sustainer. Gas generator, pump-fed. Evolved from MA-2 ICBM system. First flight 1963.
Thrust (sl): 269.000 kN (60,473 lbf). Thrust (sl): 27,430 kgf. Engine: 460 kg (1,010 lb). Chamber Pressure: 48.00 bar. Area Ratio: 25. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 83.8297872340426. Oxidizer to Fuel Ratio: 2.27. Coefficient of Thrust vacuum: 1.77414206044677. Coefficient of Thrust sea level: 1.27414206044677.
Related
- Country
- USA
- Launch Vehicles
- Atlas Agena D, Atlas F/Agena D, Atlas H, Atlas G Centaur, Atlas I
- Propellants
- Lox/Kerosene
- Stages
- Atlas Agena SLV-3A, Atlas G/H/I
- Agency
- Rocketdyne