RS-56-OBA

Hot Fire Test 72

Manufacturer Name: MA-5A. Designer: Rocketdyne. Developed in: 1988. Propellants: Lox/Kerosene. Thrust(vac): 1,046.800 kN (235,330 lbf). Thrust(sl): 920.800 kN (207,004 lbf). Isp: 299 sec. Isp (sea level): 263 sec. Burn time: 172 sec. Mass Engine: 805 kg (1,774 lb). Diameter: 2.45 m (8.03 ft). Length: 3.43 m (11.25 ft). Chambers: 1. Chamber Pressure: 48.00 bar. Area Ratio: 8.00. Oxidizer to Fuel Ratio: 2.25. Thrust to Weight Ratio: 132.30. Country: USA. Status: Out of production. First Flight: 1991. Last Flight: 2004. Flown: 126.

Designed for booster applications. Gas generator, pump-fed.

RS-56-OBA used on Rocket Stages

Used on stage: Atlas MA-5A. on launch vehicle: Atlas II.

Used on stage: Atlas MA-5A. on launch vehicle: Atlas IIA.

Used on stage: Atlas MA-5AS. on launch vehicle: Atlas IIAS.

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