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dc.contributor.authorOlds, John R.en_US
dc.date.accessioned2006-03-17T16:06:21Z
dc.date.available2006-03-17T16:06:21Z
dc.date.issued1994-04
dc.identifier.urihttp://hdl.handle.net/1853/8441
dc.description1994 Aerospace Atlantic Conference Dayton, OH, April 1994.en_US
dc.description.abstractThis paper reports the results of the second phase of a research project to characterize and optimize the design of an advanced launch vehicle for human access to low earth orbit. The vehicle makes use of rocket-based combined-cycle (RBCC) propulsion -- a concept combining operating modes of an ejector, ramjet, scramjet, and rocket in a single engine. This research builds on previous work focused on advanced multiple mode propulsion concepts and advanced conical acceleration-class single-stage-to-orbit (SSTO) launch vehicles. Three systems level design variables of interest were optimized using multidisciplinary design optimization (MDO) techniques. Specifically, Taguchi¹s method of robust design was used to identify a combination of variables that minimize the vehicle sensitivity to unpredictable changes in engine weights and performance. In addition, a second-order response surface method (RSM) was used to approximate the design space and predict the minimum dry weight vehicle. The optimized vehicle results (weights, dimensions, performance) are favorably compared with other SSTO designs including rocket and airbreathing concepts.
dc.format.extent137863 bytes
dc.format.mimetypeapplication/pdf
dc.language.isoen_US
dc.publisherGeorgia Institute of Technologyen_US
dc.relation.ispartofseriesSSDL ; SAE 94-1165en_US
dc.subjectLaunch vehicles
dc.subjectCombined cycle engines
dc.subjectLow earth orbit
dc.subjectTaguchi method
dc.subjectMultidisciplinary design optimization
dc.subjectSingle stage to orbit vehicles
dc.titleResults of a Rocket-Based Combined-Cycle SSTO Design Using Parametric; MDO Methodsen_US
dc.typePaper


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