This page no longer updated from 31 October 2001. Latest version can be found at RS-56-OBA

Hot Fire Test 72Hot Fire Test 72 - Hot firing test of Atlas rocket engine.

44,869 bytes. 1087 x 718 pixels.

Manufacturer Name: MA-5A. Designer: Rocketdyne. Developed in: 1988. Application: . Used on stages: Atlas MA-5A, Atlas MA-5AS. Used on launch vehicles: Atlas II, Atlas IIA, Atlas IIAS. Propellants: Lox/Kerosene Thrust(vac): 106,750 kgf. Thrust(vac): 1,046.80 kN. Isp: 299 sec. Isp (sea level): 263 sec. Burn time: 172 sec. Mass Engine: 805 kg. Diameter: 2.5 m. Length: 3.4 m. 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: In Production. First Flight: 1991. Last Flight: 1999. Flown: 82. Comments: Designed for booster applications. Gas generator, pump-fed.
Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .