This page no longer updated from 31 October 2001. Latest version can be found at LR-89-5

B2C/MA-1/MA-2 -

Credit: Boeing / Rocketdyne. 9,398 bytes. 167 x 205 pixels.

Manufacturer Name: MA-3. Government Designation: LR-89-5. Designer: Rocketdyne. Developed in: 1958. Application: Atlas E, F. Used on stages: Atlas MA-3, Titan Cluster. Used on launch vehicles: Atlas Centaur LV-3C, Atlas E, Atlas F, Atlas LV-3A / Agena B, Saturn B-1, SLV-3 Atlas, SLV-3 Atlas / Agena B, SLV-3 Atlas / Agena D. Propellants: Lox/Kerosene Thrust(vac): 83,870 kgf. Thrust(vac): 822.50 kN. Isp: 290 sec. Isp (sea level): 256 sec. Burn time: 120 sec. Mass Engine: 720 kg. Diameter: 2.5 m. Length: 3.4 m. Chambers: 1. Chamber Pressure: 41.00 bar. Area Ratio: 8.00. Oxidizer to Fuel Ratio: 2.25. Thrust to Weight Ratio: 116.49. Country: USA. Status: In Production. First Flight: 1960. Last Flight: 1995. Flown: 370. References: 225 . Comments: Designed for booster applications. Gas generator, pump-fed. Separate turbopumps for each booster engine.
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 .