HG-3

Advanced Engines
Credit - © Mark Wade

Designer: Rocketdyne. Propellants: Lox/LH2. Thrust(vac): 1,400.700 kN (314,890 lbf). Thrust(sl): 869.600 kN (195,494 lbf). Isp: 451 sec. Isp (sea level): 280 sec. Burn time: 324 sec. Diameter: 2.03 m (6.66 ft). Length: 2.28 m (7.48 ft). Chambers: 1. Country: USA. Status: Study 1967.

Designation for high-performance high-pressure chamber Lox/LH2 engine developed from J-2. Considered for upgrades to Saturn V launch vehicle upper stages. Technology led to Space Shuttle Main Engines.

HG-3 used on Rocket Stages

Used on stage: Saturn MS-II-2. on launch vehicle: Saturn MLV-V-3.

Used on stage: Saturn MS-II-2. on launch vehicle: Saturn V/4-260.

Used on stage: Saturn MS-IVB-2. on launch vehicle: Saturn IB-B.

Used on stage: Saturn MS-IVB-2. on launch vehicle: Saturn MLV-V-2.

Used on stage: Saturn MS-IVB-2. on launch vehicle: Saturn MLV-V-3.

HG-3 used on Spacecraft

Used on: Saturn MS-IVB-2.

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© Mark Wade, 1997 - 2007 except where otherwise noted.

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