Rocketdyne S-3D
The Rocketdyne S-3D (Air Force designation LR79) 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.
The S-3 was based on the Redstone engine, and is part of LR79 family, used on the PGM-19 Jupiter and PGM-17 Thor missiles, and on the Juno II rocket.
A second stage with four S-3 engines was considered for the Saturn A-2 study.
Its design was used later as the basis for the H-1 rocket engine of the Saturn I, and the Rolls-Royce RZ.2 of the Blue Streak.
Specifications
Rocketdyne S-3D:
- First flight: 1957
- Vehicles: PGM-19 Jupiter
- Thrust: 600.1 kN (134908 lbf).
- Specific impulse: 282 s.
- Burn time: 247 s.
Rocketdyne S-3:
- First flight: 1958
- Vehicles: Juno II, Saturn A-2
- Thrust: 667.2 kN (149993 lbf).
- Specific impulse: 282 s.
- Burn time: 182 s.
- Diameter: 2.67 m (8.75 ft).
- Dry mass: 725 kg (1,598 lb)