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astronautix.com RS-56-OSA
Delta Engine In Test
Delta Engine In Test - Hot test firing of Delta RS-56 engine.

6,664 bytes. 102 x 234 pixels.

Manufacturer Name: MA-5A. Designer: Rocketdyne. Developed in: 1988. Application: . Used on stages: Atlas II, Atlas IIA, Atlas IIAS, X-34A-1. Used on launch vehicles: Atlas II, Atlas IIA, Atlas IIAS. Propellants: Lox/Kerosene Thrust(vac): 39,400 kgf. Thrust(vac): 386.40 kN. Isp: 316 sec. Isp (sea level): 220 sec. Burn time: 283 sec. Mass Engine: 460 kg. Diameter: 3.1 m. Length: 2.7 m. Chambers: 1. Chamber Pressure: 48.00 bar. Area Ratio: 25.00. Oxidizer to Fuel Ratio: 2.25. Thrust to Weight Ratio: 85.65. Country: USA. Status: In Production. First Flight: 1991. Last Flight: 1999. Flown: 41. Comments: Designed for booster applications. Gas generator, pump-fed.
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Last update 12 March 2001.
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