RS-83

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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.

1 Overview
2 Reliability
3 Technologies
4 Timeframe
5 References
6 See also
7 External links

[edit] Overview

It was developed at Rocketdyne Propulsion and Power, located in Canoga Park, California to power the launch vehicle as part of the 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 I_sp 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 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.

[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 expendable launch systems which will be used by Project Constellation for human spaceflights to the Moon and Mars.

[edit] References

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