About: HG-3 (rocket engine)

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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 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 Satur

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  • 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 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 engine. (en)
  • HG-3は、アポロ計画の後にサターンロケットの上段用として設計された極低温液体燃料ロケットエンジンである。 アメリカのロケットダイン社によって設計されたHG-3は極低温の液体水素と液体酸素を推進剤として燃焼し、飛行中にそれぞれのエンジンの推力は1,400.7 kN (315,000 lbf)を生み出す。エンジンの比推力(Isp)は真空中で451秒または海面高度で280秒である 。、とロケットで使用する予定の改良型のとで使用するために、S-IIとS-IVBで使用されたロケットダイン社のJ-2ロケットエンジンを元に設計された。また、のために海面高度に最適化されたHG-3-SLが設計された。 アポロ計画後に進行していたサターンロケットの改良版開発が中止されたことで、HG-3の開発も中止されたが、後にスペースシャトル主エンジン(RS-25)の設計の原型として使用された。 (ja)
  • O HG-3 é um motor de foguete de combustível líquido , que foi projetado para uso nos estágios superiores dos foguetes Saturno depois do Programa Apollo. Projetado nos Estados Unidos pela Rocketdyne, o HG-3 deveria queimar uma combinação criogênica de hidrogênio líquido e oxigênio líquido como propelentes, com cada motor produzindo 1.400,7 kN de empuxo durante o voo. O motor foi projetado para gerar um impulso específico (Isp) de 451 segundos no vácuo ou 280 segundos ao nível do mar. (pt)
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  • HG-3 (en)
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  • Upper stage engine (en)
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  • Canceled (en)
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  • liquid (en)
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  • HG-3は、アポロ計画の後にサターンロケットの上段用として設計された極低温液体燃料ロケットエンジンである。 アメリカのロケットダイン社によって設計されたHG-3は極低温の液体水素と液体酸素を推進剤として燃焼し、飛行中にそれぞれのエンジンの推力は1,400.7 kN (315,000 lbf)を生み出す。エンジンの比推力(Isp)は真空中で451秒または海面高度で280秒である 。、とロケットで使用する予定の改良型のとで使用するために、S-IIとS-IVBで使用されたロケットダイン社のJ-2ロケットエンジンを元に設計された。また、のために海面高度に最適化されたHG-3-SLが設計された。 アポロ計画後に進行していたサターンロケットの改良版開発が中止されたことで、HG-3の開発も中止されたが、後にスペースシャトル主エンジン(RS-25)の設計の原型として使用された。 (ja)
  • O HG-3 é um motor de foguete de combustível líquido , que foi projetado para uso nos estágios superiores dos foguetes Saturno depois do Programa Apollo. Projetado nos Estados Unidos pela Rocketdyne, o HG-3 deveria queimar uma combinação criogênica de hidrogênio líquido e oxigênio líquido como propelentes, com cada motor produzindo 1.400,7 kN de empuxo durante o voo. O motor foi projetado para gerar um impulso específico (Isp) de 451 segundos no vácuo ou 280 segundos ao nível do mar. (pt)
  • 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 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 Satur (en)
rdfs:label
  • HG-3 (rocket engine) (en)
  • HG-3 (ロケットエンジン) (ja)
  • HG-3 (motor de foguete) (pt)
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