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 (4.42 km/s) in a vacuum, or 280 seconds (2.7 km/s) 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 MS-II-2 and MS-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 engine.
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This article is an automated import of the Wikipedia article "HG-3 (rocket engine)", available at https://en.wikipedia.org/wiki/HG-3_(rocket_engine) . Text is licensed under CC BY-SA 4.0.