MB-3-3

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

MB-3-3

Part of LR79

MB-1/MB-3
Credit: © Mark Wade

Rocketdyne LOx/Kerosene rocket engine. Out of Production. License built in Japan for H-1. First flight 1964.

Status: Out of Production. Number: 96 . Thrust: 866.70 kN (194,842 lbf). Unfuelled mass: 723 kg (1,593 lb). Specific impulse: 290 s. Specific impulse sea level: 253 s. Burn time: 270 s. Height: 1.70 m (5.50 ft). Diameter: 2.44 m (8.00 ft).

Thrust (sl): 756.100 kN (169,978 lbf). Thrust (sl): 77,104 kgf. Engine: 723 kg (1,593 lb). Chamber Pressure: 39.00 bar. Area Ratio: 8. Thrust to Weight Ratio: 122.240663900415. Coefficient of Thrust vacuum: 1.55303875500592. Coefficient of Thrust sea level: 1.35791680378641.

Country: USA. Launch Vehicles: Thor SLV-2A Agena D, Thor SLV-2A Agena B, Thor Delta D, Thor Delta E, Thor Delta G, Thor Delta J, Thor Delta N, Thor Delta M, Thorad SLV-2H Agena D, Thor Delta L, Delta 0100, H-1. Propellants: Lox/Kerosene. Stages: Delta Thor TA, Delta Thor LT, H-1-1. 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