LR87-3 (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

LR87-3

Part of LR87

LR-87-3 Engine
Credit: Bob Fortune

Aerojet LOx/Kerosene rocket engine. Titan 1 booster engine. Surplus Flight Engines were available for various uses in the 1960's. First flight 1959.

AKA: AJ23-130. Status: First flight 1959. Number: 140 . Thrust: 733.90 kN (164,987 lbf). Specific impulse: 290 s. Specific impulse sea level: 256 s. Burn time: 138 s. Height: 3.13 m (10.26 ft). Diameter: 1.53 m (5.00 ft).

Thrust (sl): 647.900 kN (145,654 lbf). Thrust (sl): 66,067 kgf. Engine: 839 kg (1,849 lb). Chamber Pressure: 40.00 bar. Area Ratio: 8. Thrust to Weight Ratio: 89.204410011919. Oxidizer to Fuel Ratio: 1.91. Coefficient of Thrust vacuum: 1.84532204931916. Coefficient of Thrust sea level: 1.64532204931916.

Country: USA. Launch Vehicles: Titan I, Super-Jupiter, Juno V-A, Juno V-B, Saturn A-1. Propellants: Lox/Kerosene. Stages: Titan 1-1. 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