This page no longer updated from 31 October 2001. Latest version can be found at LR-105-5

MA-3 -

Credit: Boeing / Rocketdyne. 10,861 bytes. 210 x 235 pixels.

Manufacturer Name: MA-3. Government Designation: LR-105-5. Designer: Rocketdyne. Developed in: 1958. Application: Atlas E, F. Used on stages: Atlas Agena SLV-3, Atlas Centaur SLV-3C/D, Atlas E/F. Used on launch vehicles: Atlas Centaur SLV-3C, Atlas Centaur SLV-3D, Atlas E, Atlas F, Atlas LV-3A / Agena B, SLV-3 Atlas, SLV-3 Atlas / Agena B, SLV-3 Atlas / Agena D. Propellants: Lox/Kerosene Thrust(vac): 39,400 kgf. Thrust(vac): 386.40 kN. Isp: 316 sec. Isp (sea level): 220 sec. Burn time: 430 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: 1960. Last Flight: 1995. Flown: 222. Comments: Atlas Sustainer. 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 .