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324:"XRS-2200 linear aerospike engine - Use of Pro/ENGINEER for determining mass properties"
248:. While the X-33 program was cancelled, two XRS-2200 engines were produced and tested.
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394:"X-33 XRS-2200 Linear Aerospike Engine Sea Level Plume Radiation"
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Rocketdyne intended to develop the subscale XRS-2200 into the
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332:American Institute of Aeronautics and Astronautics
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266:"Boeing Rocketdyne XRS-2200 Linear Aerospike"
328:35th Joint Propulsion Conference and Exhibit
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233:program. The design was based on the
16:Aerospike rocket engine by Rocketdyne
229:developed in the mid-1990s for the
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392:D'Agostino, M.G. (January 2001).
215:2.01 m (6 ft 7 in)
31:Rocketdyne XRS-2200 hotfire test
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153:1,184 kN (266,000 lb
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401:NASA Technical Reports Server
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202:339 seconds (3.32 km/s)
191:439 seconds (4.31 km/s)
165:909 kN (204,000 lb
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322:Rowbotham, Maureen (1999).
225:was an experimental linear
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180:58 bar (840 psi)
368:Encyclopedia Astronautica
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270:engineering.purdue.edu
374:on December 28, 2016
231:Lockheed Martin X-33
364:www.astronautix.com
340:10.2514/6.1999-2334
223:Rocketdyne XRS-2200
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421:Rocketdyne engines
102:Liquid-fuel engine
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298:NASA Headquarters
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162:Thrust, sea-level
37:Country of origin
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370:. Archived from
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300:. Archived from
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197:Specific impulse
186:Specific impulse
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290:"XRS-2200 Link"
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372:the original
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302:the original
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137:Nozzle ratio
96:Experimental
63:Manufacturer
246:VentureStar
199:, sea-level
145:Performance
83:Predecessor
73:Application
426:Rocketdyne
415:Categories
378:2019-08-26
360:"XRS-2200"
345:2019-09-29
308:2019-09-29
275:2019-08-26
252:References
207:Dimensions
108:Propellant
67:Rocketdyne
57:Rocketdyne
330:. U.S.:
188:, vacuum
176:pressure
174:Chamber
53:Designer
20:XRS-2200
242:RS-2200
212:Length
93:Status
397:(PDF)
122:Cycle
235:J-2S
221:The
140:58:1
87:J-2S
77:X-33
48:1999
45:Date
336:doi
116:LH2
112:LOX
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155:f
Text is available under the Creative Commons Attribution-ShareAlike License. Additional terms may apply.
