LR-91-7

Manufacturer Name: AJ23-135. Government Designation: LR91-7. Designer: Aerojet. Propellants: N2O4/Aerozine-50. Thrust(vac): 444.800 kN (99,995 lbf). Thrust(sl): 225.200 kN (50,627 lbf). Isp: 316 sec. Isp (sea level): 160 sec. Burn time: 180 sec. Mass Engine: 565 kg (1,245 lb). Diameter: 1.63 m (5.34 ft). Chambers: 1. Chamber Pressure: 50.00 bar. Area Ratio: 45.00. Oxidizer to Fuel Ratio: 1.79. Thrust to Weight Ratio: 80.28. Country: USA. Status: Study 1961. First Flight: 1962. Last Flight: 2003. Flown: 106.

Version used on Stage 2 of Gemini Launch Vehicle.

LR-91-7 used on Rocket Stages

Used on stage: Titan 2-2. on launch vehicle: Soltan.

Used on stage: Titan 2-2. on launch vehicle: Titan 2.

Used on stage: Titan LDC-2. on launch vehicle: Titan 3L2.

Used on stage: Titan LDC-2. on launch vehicle: Titan 3L4.

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 - 2007 except where otherwise noted.

Encyclopedia Astronautica
topic index
0 - A - B - C - D - E - F - G - H - I - J - K - L - M - N - O - P - Q - Ra - Re - Sa - Sf - Sp - T - U - V - W - X - Y - Z