S-3

S-3

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S-3B engine
Credit - USAF

Engine Model: S-3. Designer: Rocketdyne. Propellants: Lox/Kerosene. Thrust(vac): 758.700 kN (170,563 lbf). Thrust(sl): 667.200 kN (149,993 lbf). Isp: 282 sec. Isp (sea level): 248 sec. Burn time: 182 sec. Mass Engine: 725 kg (1,598 lb). Diameter: 2.67 m (8.75 ft). Chambers: 1. Chamber Pressure: 39.50 bar. Area Ratio: 8.00. Thrust to Weight Ratio: 106.71. Country: USA. Status: Study 1959. First Flight: 1958. Last Flight: 1961. Flown: 10.

Engine Model: S-3-20M5A. Designer: Dushkin. Developed in: -1959. Application: U-21. Propellants: Nitric acid/Kerosene. Thrust(sl): 29.400 kN (6,609 lbf). Country: Russia. Status: Developed -1959.

Engine Model: S-3D. Manufacturer Name: S-3D. Designer: Rocketdyne. Developed in: 1955. Propellants: Lox/Kerosene. Thrust(sl): 600.100 kN (134,908 lbf). Isp (sea level): 247 sec. Country: USA. First Flight: 1957.

Jupiter Booster. Gas generator, pump-fed. Thrust later 150,000 lbs. Thrust and specific impulse values are at sea level.

S-3 used on Rocket Stages

Used on stage: Jupiter. on launch vehicle: Jupiter.

Used on stage: Jupiter Cluster. on launch vehicle: Saturn I.

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© Mark Wade, 1997 - 2008 except where otherwise noted.