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The Rocketdyne S-3D (Air Force designation LR79) is an American liquid rocket engine produced by 
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.
Rocketdyne
Rocketdyne is an American rocket engine design and production company headquartered in Canoga Park, California, Canoga Park, in the western San Fernando Valley of suburban Los Angeles, California, Los Angeles, in southern California.
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
RP-1 (Rocket Propellant-1 or Refined Petroleum-1) and similar fuels like RG-1 and T-1 are highly refined kerosene formulations used as rocket fuel. Liquid-fueled rockets that use RP-1 as fuel are known as kerolox rockets. In their engines, RP- ...
(kerosene) propellant combination, capable of producing 134,908 pounds of thrust (600.1 kN) at sea level.
The S-3 was based on the Redstone engine, and is part of the LR79 family, used on the PGM-19 Jupiter
The PGM-19 Jupiter was the first nuclear weapon, nuclear armed, medium-range ballistic missile (MRBM) of the United States Air Force (USAF). It was a liquid-propellant rocket using RP-1 fuel and Liquid oxygen, LOX oxidizer, with a single Rocketd ...
and PGM-17 Thor
The PGM-17A Thor was the first operative ballistic missile of the United States Air Force (USAF). It was named after the Thor, Norse god of thunder. It was deployed in the United Kingdom between 1959 and September 1963 as an intermediate-range b ...
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
The PGM-19 Jupiter was the first nuclear weapon, nuclear armed, medium-range ballistic missile (MRBM) of the United States Air Force (USAF). It was a liquid-propellant rocket using RP-1 fuel and Liquid oxygen, LOX oxidizer, with a single Rocketd ...
* 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)
References
{{Rocket engines S-3D Rocket engines of the United States Rocket engines using the gas-generator cycle