Title:
System Sensitivity Analysis Applied to the Conceptual Design of a Dual-Fuel Rocket SSTO

dc.contributor.author Olds, John R. en_US
dc.contributor.corporatename American Institute of Aeronautics and Astronautics
dc.date.accessioned 2006-03-17T16:04:27Z
dc.date.available 2006-03-17T16:04:27Z
dc.date.issued 1994-09
dc.description 5th AIAA/USAF/NASA/ISSMO; Symposium on Multidisciplinary Analysis and Optimization Panama City, Fl, September 1994. en_US
dc.description.abstract This paper reports the results of initial efforts to apply the System Sensitivity Analysis (SSA) optimization method to the conceptual design of a single-stage-to-orbit (SSTO) launch vehicle. SSA is an efficient, calculus-based MDO technique for generating sensitivity derivatives in a highly multidisciplinary design environment. The method has been successfully applied to conceptual aircraft design and has been proven to have advantages over traditional direct optimization methods. The method is applied to the optimization of an advanced, piloted SSTO design similar to vehicles currently being analyzed by NASA as possible replacements for the Space Shuttle. Powered by a derivative of the Russian RD-701 rocket engine, the vehicle employs a combination of hydrocarbon, hydrogen, and oxygen propellants. Three primary disciplines are included in the design --- propulsion, performance, and weights & sizing. A complete, converged vehicle analysis depends on the use of three standalone conceptual analysis computer codes. Efforts to minimize vehicle dry (empty) weight are reported in this paper. The problem consists of six system-level design variables and one system-level constraint, Using SSA in a "manual" fashion to generate gradient information, six system-level iterations were performed from each of two different starting points. The results showed a good pattern of convergence for both starting points. A discussion of the advantages and disadvantages of the method, possible areas of improvement, and future work is included.
dc.format.extent 100746 bytes
dc.format.mimetype application/pdf
dc.identifier.uri http://hdl.handle.net/1853/8440
dc.language.iso en_US
dc.publisher Georgia Institute of Technology en_US
dc.publisher.original American Institute of Aeronautics and Astronautics (AIAA)
dc.relation.ispartofseries SSDL ; AIAA 94-4339 en_US
dc.subject Conceptual design
dc.subject Sensitivity analysis
dc.subject Single stage to orbit vehicles
dc.subject Multidisciplinary design optimization
dc.title System Sensitivity Analysis Applied to the Conceptual Design of a Dual-Fuel Rocket SSTO en_US
dc.type Text
dc.type.genre Paper
dspace.entity.type Publication
local.contributor.corporatename Space Systems Design Laboratory (SSDL)
local.contributor.corporatename Daniel Guggenheim School of Aerospace Engineering
local.contributor.corporatename Daniel Guggenheim School of Aerospace Engineering
relation.isOrgUnitOfPublication dc68da3d-4cfe-4508-a4b0-35ba8de923fb
relation.isOrgUnitOfPublication a348b767-ea7e-4789-af1f-1f1d5925fb65
relation.isOrgUnitOfPublication a348b767-ea7e-4789-af1f-1f1d5925fb65
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