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・ RS Technologies
・ RS Telescopii
・ RS Tera
・ RS Vareo
・ RS Venture
・ RS Vision
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・ RS-102221
・ RS-122
・ RS-127445
・ RS-18
・ RS-232
・ RS-24 Yars
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RS-27A
・ RS-28 Sarmat
・ RS-422
・ RS-423
・ RS-449
・ RS-485
・ RS-56812
・ RS-67,333
・ RS-68
・ RS-82 (rocket family)
・ RS-83
・ RS-88
・ RS/6000
・ RS100
・ Rs1799913


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RS-27A : ウィキペディア英語版
RS-27A

The RS-27A is a liquid-fuel rocket engine developed by Rocketdyne for use on the first stage of the Delta II and Delta III launch vehicles. It provides of thrust burning RP-1 and LOX in a gas-generator cycle. The engine is a modified version of its predecessor, the RS-27;〔(Astronautix: RS-27 Engine )〕 its thrust nozzle has been extended to increase its area ratio from 8:1 to 12:1, which provides greater efficiency at altitude. The earlier RS-27 was derived from surplus Rocketdyne H-1 engines used in the Saturn 1B launcher.〔(Astronautix: RS-27 Derivation on Delta )〕
The RS-27A main engine is neither restartable nor throttleable. In addition to its main engine, the RS-27A includes two vernier engines to provide vehicle roll control during flight. The RS-27A has a run duration of 265 seconds.
==References==


抄文引用元・出典: フリー百科事典『 ウィキペディア(Wikipedia)
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