Rocketdyne S-3D
| File:S-3 D Jupiter engine restored.jpg S-3D engine at the National Air and Space Museum | |
| 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] was 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 134,908 pounds of thrust (600.1 kN) at sea level.[3]
The S-3 was based on the Redstone engine,[4] and is part of the 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] Other members of the LR79 engine family include: XLR71-NA-1, B-2C, XLR83-NA-1, LR79-7, S-3D, XLR89-1, MB-3-1, X-1, LR83-NA-1, H-1, LR89-5, XLR89-5, S-3, LR89-7, MB-3-J, MB-3, MB-3-3, RZ.2, H-1c, H-1b, RS-27, RS-27A R, RS-56-OBA and RS-27C.[5]
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.
Specifications
[edit | edit source]Rocketdyne S-3D:[3]
- First flight: 1957
- Vehicles: PGM-19 Jupiter
- Thrust: 600.1 kN (134908 lbf).
- Specific impulse: 282 s.
- Burn time: 247 s.
Rocketdyne S-3: [14]
- First flight: 1958
- Vehicles: Juno II, Saturn A-2[12]
- 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
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