Country of origin | United States |
---|---|
Manufacturer | Rocketdyne |
Application | Booster |
Successor | H-1 |
Status | Retired |
Liquid-fuel engine | |
Propellant | LOX / RP-1 |
Cycle | Gas Generator |
Configuration | |
Chamber | 1 |
Performance | |
Thrust, sea-level | 134908 lbf (600.1 kN) |
Specific impulse, sea-level | 247 seconds (2.42 km/s) |
Used in | |
PGM-19 Jupiter, PGM-17 Thor, Juno II, Saturn A-2 |
The Rocketdyne S-3D (Air Force designation LR79)[1][2] is an American liquid rocket engine produced by Rocketdyne (a division of North American Aviation) between 1956 and 1961. It was a gas generator, pump-fed engine, using a liquid oxygen (LOX) and RP-1 (kerosene) propellant combination, capable of producing 134908 pounds of thrust (600.1 kN) at sea level.[3]
The S-3 was based on the Redstone engine,[4] and is part of LR79 family,[5][6][1][2] used on the PGM-19 Jupiter and PGM-17 Thor missiles,[7][4][8] and on the Juno II rocket.[3][9][10][11]
A second stage with four S-3 engines was considered for the Saturn A-2 study.[12]
Its design was used later as the basis for the H-1 rocket engine of the Saturn I,[13][1][7] and the Rolls-Royce RZ.2 of the Blue Streak.