Credit: Boeing / Rocketdyne
Rocketdyne Lox/Kerosene rocket engine for Delta 7000. 1054.2 kN. Isp=302s. First flight 1990.
Thrust (sl): 890.100 kN (200,102 lbf). Thrust (sl): 90,768 kgf. Engine: 1,091 kg (2,405 lb). Chamber Pressure: 48.00 bar. Area Ratio: 12. Thrust to Weight Ratio: 98.5320652356858. Oxidizer to Fuel Ratio: 2.245. Coefficient of Thrust vacuum: 1.47249461844616. Coefficient of Thrust sea level: 1.22249461844616.
Unfuelled mass: 1,091 kg (2,405 lb).
More... - Chronology...
Height: 3.78 m (12.40 ft).
Diameter: 2.44 m (8.00 ft).
Thrust: 1,054.20 kN (236,994 lbf).
Specific impulse: 302 s.
Specific impulse sea level: 255 s.
Burn time: 265 s.
Number: 107 .
Associated Launch Vehicles
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Associated Manufacturers and Agencies
Lox/Kerosene Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. In January 1953 Rocketdyne commenced the REAP program to develop a number of improvements to the engines being developed for the Navaho and Atlas missiles. Among these was development of a special grade of kerosene suitable for rocket engines. Prior to that any number of rocket propellants derived from petroleum had been used. Goddard had begun with gasoline, and there were experimental engines powered by kerosene, diesel oil, paint thinner, or jet fuel kerosene JP-4 or JP-5. The wide variance in physical properties among fuels of the same class led to the identification of narrow-range petroleum fractions, embodied in 1954 in the standard US kerosene rocket fuel RP-1, covered by Military Specification MIL-R-25576. In Russia, similar specifications were developed for kerosene under the specifications T-1 and RG-1. The Russians also developed a compound of unknown formulation in the 1980's known as 'Sintin', or synthetic kerosene. More...
Delta Thor XLT-C Lox/Kerosene propellant rocket stage. Loaded/empty mass 101,900/5,900 kg. Thrust 1,054.20 kN. Vacuum specific impulse 302 seconds. More...
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