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The RS-83 was a rocket engine design for a reusable liquid hydrogen/liquid oxygen rocket larger and more powerful than any other. The RS-83 was designed to last 100 missions, and was intended for use on the first stage of a two-stage-to-orbit reusable launch vehicle. == Development == It was developed by Rocketdyne Propulsion and Power, located in Canoga Park, California to power the launch vehicle as part of the Space Launch Initiative (SLI) program. This engine was designed to produce a thrust of at sea level and in a vacuum with an ''I''sp of 395 and 446 seconds (3.87 and 4.37 kN·s/kg), respectively. The engine was designed to use many new technologies including ones developed for the Space Shuttle Main Engine (SSME). Technologies include channel wall regenerative nozzles, hydrostatic bearings, and turbine damping. The RS-83 is loosely based on the RS-68 that powers the Delta IV expendable launch vehicle. The RS-83 design is more efficient, lighter, slightly stronger, and yet reusable. The engine design weight was 12,700 lb (5,760 kg) with an engine thrust to weight ratio of 52:1 at launch. One of the main goals of SLI was to develop components of a reusable launch vehicle with high reliability. The RS-83 was designed for a loss of vehicle rate of 1 in 1,000. Another goal of the program was to dramatically reduce the cost per unit weight of payload to low earth orbit. The RS-83 was designed with the goal of $1,000/lb ($2,200/kg). The engine passed numerous design reviews and was on schedule for prototype testing in 2005 before the SLI program was cancelled. NASA changed its focus to expendable launch systems used in the Constellation program for human spaceflights to the Moon and Mars. The Air Force Reusable Booster System program may renew interest in further development.〔(【引用サイトリンク】publisher=RLV and Space Transport News )〕 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「RS-83」の詳細全文を読む スポンサード リンク
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