Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
LR105-7
Part of LR105 Family
MA-5
MA-5
Credit: Boeing / Rocketdyne
Rocketdyne LOx/Kerosene rocket engine. Atlas space launchers. Out of production. Atlas Sustainer. Gas generator, pump-fed. Evolved from MA-2 ICBM system. First flight 1963.

Status: Out of production. Date: 1960. Number: 50 . Thrust: 386.40 kN (86,866 lbf). Specific impulse: 316 s. Specific impulse sea level: 220 s. Burn time: 266 s. Height: 2.69 m (8.82 ft). Diameter: 3.05 m (10.00 ft).

Thrust (sl): 269.000 kN (60,473 lbf). Thrust (sl): 27,430 kgf. Engine: 460 kg (1,010 lb). Chamber Pressure: 48.00 bar. Area Ratio: 25. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 83.8297872340426. Oxidizer to Fuel Ratio: 2.27. Coefficient of Thrust vacuum: 1.77414206044677. Coefficient of Thrust sea level: 1.27414206044677.



Country: USA. Launch Vehicles: Atlas Agena D, Atlas F/Agena D, Atlas H, Atlas G Centaur, Atlas I. Propellants: Lox/Kerosene. Stages: Atlas Agena SLV-3A, Atlas G/H/I. Agency: Rocketdyne.

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2017 Mark Wade - Contact
© / Conditions for Use