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Development of Approximations for HSCT Wing Bending Material Weight using Response Surface Methodology

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dc.contributor.authorBalabanov, Vladimir Olegovichen
dc.contributor.committeechairHaftka, Raphael T.en
dc.contributor.committeememberMason, William H.en
dc.contributor.committeememberKapania, Rakesh K.en
dc.contributor.committeememberWatson, Layne T.en
dc.contributor.committeememberGrossman, Bernard M.en
dc.contributor.committeememberHughes, Owen F.en
dc.contributor.departmentAerospace and Ocean Engineeringen
dc.date.accessioned2014-03-14T20:22:37Zen
dc.date.adate1997-10-01en
dc.date.available2014-03-14T20:22:37Zen
dc.date.issued1997-05-09en
dc.date.rdate1997-10-01en
dc.date.sdate1997-05-09en
dc.description.abstractA procedure for generating a customized weight function for wing bending material weight of a High Speed Civil Transport (HSCT) is described. The weight function is based on HSCT configuration parameters. A response surface methodology is used to fit a quadratic polynomial to data gathered from a large number of structural optimizations. To reduce the time of performing a large number of structural optimizations, coarse-grained parallelization with a master-slave processor assignment on an Intel Paragon computer is used. The results of the structural optimization are noisy. Noise reduction in the structural optimization results is discussed. It is shown that the response surface filters out this noise. A statistical design of experiments technique is used to minimize the number of required structural optimizations and to maintain accuracy. Simple analysis techniques are used to find regions of the design space where reasonable HSCT designs could occur, thus customizing the weight function to the design requirements of the HSCT, while the response surface itself is created employing detailed analysis methods. Analysis of variance is used to reduce the number of polynomial terms in the response surface model function. Linear and constant corrections based on a small number of high fidelity results are employed to improve the accuracy of the response surface model. Configuration optimization of the HSCT employing a customized weight function is compared to the configuration optimization of the HSCT with a general weight function.en
dc.description.degreePh. D.en
dc.identifier.otheretd-82597-124631en
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-82597-124631/en
dc.identifier.urihttp://hdl.handle.net/10919/30730en
dc.publisherVirginia Techen
dc.relation.haspartDisser.pdfen
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subjectStructural optimizationen
dc.subjectOptimizationen
dc.subjectFinite element analysisen
dc.subjectFinite element optimizationen
dc.subjectDesignen
dc.subjectResponse Surfaceen
dc.subjectDesign of experimentsen
dc.subjectMultidisciplinary optimizationen
dc.subjectParallel computingen
dc.titleDevelopment of Approximations for HSCT Wing Bending Material Weight using Response Surface Methodologyen
dc.typeDissertationen
thesis.degree.disciplineAerospace and Ocean Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.leveldoctoralen
thesis.degree.namePh. D.en

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