LR105 home
topic index
Engine Model: LR105-3. Government Designation: LR105-3. Designer: Rocketdyne. Propellants: Lox/Kerosene. Thrust(vac): 375.000 kN (84,303 lbf). Thrust(sl): 267.000 kN (60,023 lbf). Isp: 308 sec. Isp (sea level): 220 sec. Chambers: 1. Chamber Pressure: 50.30 bar. Oxidizer to Fuel Ratio: 2.27. Country: USA. Status: Out of Production.

Early version of Atlas Sustainer. Gas generator, pump-fed.

Engine Model: LR105-5. Manufacturer Name: MA-3. Government Designation: LR105-5. Designer: Rocketdyne. Developed in: 1958. Application: Atlas E, F. 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: 430 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. First Flight: 1960. Last Flight: 1995. Flown: 289.

Atlas Sustainer. Gas generator, pump-fed. Separate turbopumps for each booster engine.

Engine Model: LR105-7. 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.

Engine Model: RS-56-OSA. 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.

Engine Model: S-4. Designer: Rocketdyne. Developed in: 1957. Propellants: Lox/Kerosene. Thrust(vac): 412.800 kN (92,801 lbf). Chambers: 1. Country: USA. Status: Design ca. 1957.

Version of Atlas sustainer tailored to Redstone Arsenal upper-stage requirements. Paper study only.

Engine Model: XLR105-5. Manufacturer Name: MA-2. Government Designation: XLR105-5. Designer: Rocketdyne. Developed in: 1958. Application: Atlas D. Propellants: Lox/Kerosene. Thrust(vac): 363.200 kN (81,651 lbf). Thrust(sl): 252.700 kN (56,809 lbf). Isp: 309 sec. Isp (sea level): 215 sec. Burn time: 335 sec. Mass Engine: 460 kg (1,010 lb). Diameter: 3.05 m (10.00 ft). Chambers: 1. Chamber Pressure: 48.00 bar. Area Ratio: 25.00. Thrust to Weight Ratio: 80.52. Country: USA. First Flight: 1958. Last Flight: 1967. Flown: 172.

Atlas Sustainer. Gas generator, pump-fed. Shared turbopumps for booster engines.

LR105 used on Rocket Stages
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 - 2008 except where otherwise noted.