RS-56-OSA

Delta Engine In Test

Manufacturer Name: MA-5A. Designer: Rocketdyne. Developed in: 1988. Propellants: Lox/Kerosene. Thrust(vac): 386.400 kN (86,866 lbf). Thrust(sl): 269.000 kN (60,473 lbf). Isp: 316 sec. Isp (sea level): 220 sec. Burn time: 283 sec. Mass Engine: 460 kg (1,010 lb). Diameter: 3.05 m (10.00 ft). Length: 2.70 m (8.80 ft). 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: Out of production. First Flight: 1991. Last Flight: 2004. Flown: 63.

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

RS-56-OSA used on Rocket Stages

Used on stage: Atlas II. on launch vehicle: Atlas II.

Used on stage: Atlas IIA. on launch vehicle: Atlas IIA.

Used on stage: Atlas IIAS. on launch vehicle: Atlas IIAS.

Used on stage: X-34A-1. on launch vehicle: X-34A.

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