Encyclopedia Astronautica

Credit: © Mark Wade
LR-79 Engine
Credit: Bob Fortune
Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Out of production. Designed for booster applications. Gas generator, pump-fed. Isp=282s. First flight 1957.

Thrust (sl): 667.200 kN (149,993 lbf). Thrust (sl): 68,039 kgf. Engine: 643 kg (1,417 lb). Chamber Pressure: 41.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 120.321928460342. Coefficient of Thrust vacuum: 1.25036300393336. Coefficient of Thrust sea level: 1.05524105271385.

AKA: LR79--NA-7.
Status: Out of production..
Diameter: 1.53 m (5.00 ft).
Thrust: 758.70 kN (170,563 lbf).
Specific impulse: 282 s.
Specific impulse sea level: 248 s.
Burn time: 165 s.
First Launch: 1955.
Number: 268 .

More... - Chronology...

Associated Countries
See also
Associated Launch Vehicles
  • Thor American liquid propellant intermediate range ballistic missile, developed by Douglas in 1956-1958. 60 deployed to Britain in 1958-1962. The basis for a family of Thor and Delta space launch vehicles, remaining in production into the 2010's. More...
  • Delta American orbital launch vehicle. The Delta launch vehicle was America's longest-lived, most reliable, and lowest-cost space launch vehicle. Delta began as Thor, a crash December 1955 program to produce an intermediate range ballistic missile using existing components, which flew thirteen months after go-ahead. Fifteen months after that, a space launch version flew, using an existing upper stage. The addition of solid rocket boosters allowed the Thor core and Able/Delta upper stages to be stretched. Costs were kept down by using first and second-stage rocket engines surplus to the Apollo program in the 1970's. Continuous introduction of new 'existing' technology over the years resulted in an incredible evolution - the payload into a geosynchronous transfer orbit increasing from 68 kg in 1962 to 3810 kg by 2002. Delta survived innumerable attempts to kill the program and replace it with 'more rationale' alternatives. By 2008 nearly 1,000 boosters had flown over a fifty-year career, and cancellation was again announced. More...
  • Thor Able American orbital launch vehicle. Thor with Able stage derived from Vanguard second stage. More...
  • Thor Agena A American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x Agena A More...
  • Thor Agena B American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-21 + 1 x Agena B More...
  • Thor Agena D American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-21 + 1 x Agena D More...
  • Thor Burner American orbital launch vehicle. Thor DM-18A with 'Burner' upper stage solid rocket packages used for launch of classified payloads. More...

Associated Manufacturers and Agencies
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...

Associated Stages
  • 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. More...

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