RS-83
From Wikipedia, the free encyclopedia
The RS-83 was a design for the largest and most powerful liquid hydrogen/liquid oxygen rocket engine to be built. The RS-83 is a reusable engine designed to last 100 missions, and was intended to be one possible alternative to the first stage of a two-stage-to-orbit reusable launch vehicle.
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[edit] Overview
It was developed at Rocketdyne Propulsion and Power, located in Canoga Park, California to power the launch vehicle as part of NASA's now cancelled Space Launch Initiative. This engine was designed to produce a thrust of 664,000 lbf at sea level and 750,000 lbf in a vacuum ((2.95 and 3.34 MN) with an Isp of 395 and 446 seconds (3.87 and 4.37 kN·s/kg), respectively. 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 reusable though. The engine design weight was 12,700 lb (5,760 kg) with an engine thrust to weight ratio of 52:1 at launch.
[edit] Reliability
One of the main goals of the Space Launch Initiative 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 pound of payload to low earth orbit. The RS-83 was designed with the goal of $1,000/lb ($2,200/kg).
[edit] Technologies
This 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.
[edit] Timeframe
The engine passed numerous design reviews and was on schedule for prototype testing in 2005 before the program was cancelled. NASA is now focusing on heavy lift expendable launchers needed for human Moon and Mars missions.
