Encyclopedia Astronautica
Thor DM-19


Lox/Kerosene propellant rocket stage. Loaded/empty mass 49,340/3,125 kg. Thrust 758.71 kN. Vacuum specific impulse 282 seconds.

Cost $ : 4.930 million.

Status: Retired 1980.
Gross mass: 49,340 kg (108,770 lb).
Unfuelled mass: 3,125 kg (6,889 lb).
Height: 18.42 m (60.43 ft).
Diameter: 2.44 m (8.00 ft).
Span: 2.44 m (8.00 ft).
Thrust: 758.71 kN (170,565 lbf).
Specific impulse: 282 s.
Specific impulse sea level: 248 s.
Burn time: 165 s.
Number: 224 .

More... - Chronology...


Associated Countries
Associated Engines
  • LR79-7 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Out of production. Designed for booster applications. Gas generator, pump-fed. Isp=282s. First flight 1957. More...

Associated Launch Vehicles
  • Thor DM-18 American orbital launch vehicle. Single stage vehicle adapted from Thor IRBM with no upper stage. More...
  • Thor Able American orbital launch vehicle. Thor with Able stage derived from Vanguard second stage. More...
  • Thor Able I American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x Able 1/AJ10-41 + 1 x Altair More...
  • Thor Agena A American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x Agena A More...
  • Thor Able II American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x Able 2/AJ10-42 More...
  • Thor Able III American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x Able 3/AJ10 + 1 x Altair More...
  • Thor Able II M1 American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x Able 2/AJ10-42 + 1 x Altair More...
  • Thor Able IV American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x AJ10 + 1 x Altair More...
  • Thor Delta American orbital launch vehicle. Commercial name for the military's Thor-Delta. The name of the Delta second stage eventually was applied to subsequent commercial follow-ons. More...
  • Thor DSV-2G American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x AJ10-118 More...
  • Thor MG-18 American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x MG-18 More...
  • Thor Burner 1 American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x FW4S More...
  • Thor Burner 2 American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x Star 37B More...
  • Thor Burner 2A American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x Star 37B + 1 x Star 26B More...

Associated Propellants
  • 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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