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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
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expendable launch vehicle. The RS-83 design is more efficient, lighter, slightly stronger, and yet reusable. The engine design weight was 12,700 pounds (5,800 kg) with an engine
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184:(SLI) program. This engine was designed to produce a thrust of 664,000 lbf (2,950 kN) at sea level and 750,000 lbf (3,300 kN) in a vacuum with an
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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
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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
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The engine was designed to use many new technologies including ones developed for the
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of 395 seconds (3.87 km/s) and 446 seconds (4.37 km/s) respectively.
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295:"Boeing Rocketdyne Chooses Design for Next-Generation Reusable Rocket Engine"
271:"Main Engine Candidates for a Second Generation Reusable Launch Vehicle"
297:(Press release). Boeing Rocketdyne. January 28, 2002. Archived from
221:. The RS-83 was designed with the goal of $ 1,000/lb ($ 2,200/kg).
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Proposed hydrolox rocket engine intended to surpass the RS-68
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331:Rocket engines using the gas-generator cycle
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180:to power the launch vehicle as part of the
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276:. NASA. September 2002. Archived from
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346:Rocket engines of the United States
201:The RS-83 is loosely based on the
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176:Propulsion and Power, located in
110:750,000 lbf (3,300 kN)
49:Pratt & Whitney Rocketdyne
39:Pratt & Whitney Rocketdyne
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134:12,700 pounds (5,800 kg)
121:446 seconds (4.37 km/s)
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316:Stennis Space Center page.
226:expendable launch systems
196:Space Shuttle Main Engine
160:of a two-stage-to-orbit
182:Space Launch Initiative
178:Canoga Park, California
162:reusable launch vehicle
236:to the Moon and Mars.
211:thrust to weight ratio
148:design for a reusable
230:Constellation program
172:It was developed by
246:J-2 (rocket engine)
96:Gas-generator cycle
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336:Rocketdyne engines
234:human spaceflights
72:Liquid-fuel engine
213:of 52 at launch.
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25:Country of origin
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301:on June 4, 2011.
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45:Manufacturer
168:Development
102:Performance
58:first stage
55:Application
325:Categories
257:References
174:Rocketdyne
126:Dimensions
78:Propellant
66:prototype
240:See also
207:Delta IV
131:Dry mass
118:, vacuum
35:Designer
144:was a
63:Status
281:(PDF)
274:(PDF)
251:RS-84
203:RS-68
158:stage
142:RS-83
92:Cycle
20:RS-83
232:for
140:The
86:LH2
82:LOX
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189:sp
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186:I
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