HG-3 (rocket engine)
|Country of origin||United States|
|Application||Upper stage engine|
|Associated L/V||Saturn MLV
|Status||Cancelled during development.|
|Propellant||Liquid oxygen / Liquid hydrogen|
|Thrust (vac.)||1,400.7 kN (314,900 lbf)|
|Thrust (SL)||869.6 kN (195,500 lbf)|
|Isp (vac.)||451 seconds (4.42 km/s)|
|Isp (SL)||280 seconds (2.7 km/s)|
The HG-3 was a liquid-fuel cryogenic rocket engine which was designed for use on the upper stages of Saturn rockets in the post-Apollo era. Designed in the United States by Rocketdyne, the HG-3 was to have burned cryogenic liquid hydrogen and liquid oxygen propellants, with each engine producing 1,400.7 kN (315,000 lbf) of thrust during flight. The engine was designed to produce a specific impulse (Isp) of 451 seconds in a vacuum, or 280 seconds at sea level. Developed from Rocketdyne's J-2 engine used on the S-II and S-IVB stages, the engine was intended to replace the J-2 on the upgraded S-II-2 and S-IVB-2 stages intended for use on the Saturn MLV, Saturn IB-B and Saturn V/4-260 rockets, with a sea-level optimised version, the HG-3-SL, intended for use on the Saturn INT-17. The engine was cancelled, however, during the post-Apollo drawdown when development of the more advanced Saturn rockets ceased, and never flew, although the engine was later used as the basis for the design of the RS-25 Space Shuttle main engine.
- Mark Wade (17 November 2011). "HG-3". Encyclopedia Astronautica. Retrieved 18 February 2012.
- Mark Wade (17 November 2011). "HG-3-SL". Encyclopedia Astronautica. Retrieved 18 February 2012.
- "MSFC Propulsion Center of Excellence is Built on Solid Foundation". NASA. 1995. Retrieved 13 December 2011.
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