Lox/Kerosene propellant rocket stage. Loaded/empty mass 85,800/4,400 kg. Thrust 866.71 kN. Vacuum specific impulse 290 seconds. License built MB-3 ELT Thor
Cost $ : 30.000 million.
AKA: Extended Length Tank Thor MB-3.
More... - Chronology...
Status: Retired 1992.
Gross mass: 85,800 kg (189,100 lb).
Unfuelled mass: 4,400 kg (9,700 lb).
Height: 22.00 m (72.00 ft).
Diameter: 2.44 m (8.00 ft).
Span: 2.44 m (8.00 ft).
Thrust: 866.71 kN (194,844 lbf).
Specific impulse: 290 s.
Specific impulse sea level: 253 s.
Burn time: 270 s.
Number: 21 .
MB-3-3 Rocketdyne Lox/Kerosene rocket engine. 866.7 kN. Out of Production. License built in Japan for H-1. Isp=290s. First flight 1964. More...
Associated Launch Vehicles
N-2 Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle. More...
H-1 Japanese license-built version of Delta launch vehicle, with Japanese-developed upper stages. More...
H-1 (2) American orbital launch vehicle. Three stage version consisting of 9 x Castor 2 + 1 x ELT Thor N + 1 x LE-5 More...
H-1 6R American orbital launch vehicle. Four stage version consisting of 6 x Castor 2 + 1 x ELT Thor N + 1 x LE-5 + 1 x UM129A More...
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...
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