LR-105-7

MA-5
Credit - Boeing / Rocketdyne

Manufacturer Name: MA-5. Government Designation: LR105-7. Designer: Rocketdyne. Developed in: 1960. Application: Atlas space launchers. 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: 266 sec. Mass Engine: 460 kg (1,010 lb). Diameter: 3.05 m (10.00 ft). Length: 2.69 m (8.82 ft). Chambers: 1. Chamber Pressure: 48.00 bar. Area Ratio: 25.00. Oxidizer to Fuel Ratio: 2.27. Thrust to Weight Ratio: 83.83. Country: USA. Status: Out of production. First Flight: 1963. Last Flight: 1997. Flown: 50.

Atlas Sustainer. Gas generator, pump-fed. Evolved from MA-2 ICBM system.

LR-105-7 used on Rocket Stages

Used on stage: Atlas Agena SLV-3A. on launch vehicle: Atlas / Agena D SLV-3A.

Used on stage: Atlas Agena SLV-3A. on launch vehicle: Atlas LV-3A / Agena D.

Used on stage: Atlas G/H/I. on launch vehicle: Atlas G.

Used on stage: Atlas G/H/I. on launch vehicle: Atlas H.

Used on stage: Atlas G/H/I. on launch vehicle: Atlas I.

Contact us with any corrections, additions, or comments.

Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.

© Mark Wade, 1997 - 2007 except where otherwise noted.

Encyclopedia Astronautica
topic index
0 - A - B - C - D - E - F - G - H - I - J - K - L - M - N - O - P - Q - Ra - Re - Sa - Sf - Sp - T - U - V - W - X - Y - Z