LR91-7 (original) (raw)

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

LR91-7

Part of LR91

Aerojet N2O4/Aerozine-50 rocket engine. Version used on Stage 2 of Gemini Titan 2 Launch Vehicle. Proposed for unflown Titan 3L2, Titan 3L4 boosters. First flight 1962.

AKA: AJ23-135. Status: First flight 1962.. Number: 106 . Thrust: 444.80 kN (99,995 lbf). Specific impulse: 316 s. Specific impulse sea level: 160 s. Burn time: 180 s. Diameter: 1.63 m (5.34 ft).

Thrust (sl): 225.200 kN (50,627 lbf). Thrust (sl): 22,967 kgf. Engine: 565 kg (1,245 lb). Chamber Pressure: 50.00 bar. Area Ratio: 45. Thrust to Weight Ratio: 80.2814159292035. Oxidizer to Fuel Ratio: 1.79. Coefficient of Thrust vacuum: 2.07098641649344. Coefficient of Thrust sea level: 1.17098641649344.

Family: Storable liquid. Country: USA. Launch Vehicles: Titan II, Titan 3L2, Titan 3L4. Propellants: N2O4/Aerozine-50. Stages: Titan 2-2, Titan LDC-2. Agency: Aerojet.

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