RS-56-OBA
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Hot firing test of Atlas rocket engine.
Rocketdyne LOx/Kerosene rocket engine. Out of production. Designed for booster applications. Gas generator, pump-fed. Booster engine for Atlas II, IIA, IIAS. First flight 1991.
Thrust (sl): 920.800 kN (207,004 lbf). Thrust (sl): 93,897 kgf. Engine: 805 kg (1,774 lb). Chamber Pressure: 48.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 132.298136645963. Oxidizer to Fuel Ratio: 2.25. Coefficient of Thrust vacuum: 1.545. Coefficient of Thrust sea level: 1.37.
Related
- Country
- USA
- Launch Vehicles
- Atlas II, Atlas IIA, Atlas IIAS
- Propellants
- Lox/Kerosene
- Stages
- Atlas MA-5A, Atlas MA-5AS
- Agency
- Rocketdyne