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
Plug-Nozzle SSME
Notional LOx/LH2 rocket engine. Study 1978. Used on VTOVL launch vehicle.

Status: Study 1978. Thrust: 3,728.70 kN (838,245 lbf). Unfuelled mass: 2,973 kg (6,554 lb). Specific impulse: 485 s. Specific impulse sea level: 412 s. Burn time: 500 s.

Thrust (sl): 3,167.400 kN (712,060 lbf). Thrust (sl): 322,992 kgf. Engine: 2,973 kg (6,554 lb). Area Ratio: 600. Thrust to Weight Ratio: 127.89.



Country: USA. Launch Vehicles: VTOVL 1978. Propellants: Lox/LH2. Stages: VTOVL 150t.

Back to top of page
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
© 1997-2019 Mark Wade - Contact
© / Conditions for Use