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dc.contributor.advisorSamson, Charles H.
dc.creatorStebbins, Frederick Jean
dc.description.abstractA composite laminated torispherical shell was idealized as a network of curved beams. A stiffness matrix method was developed in torispherical coordinates which are amenable to the current family of manned spacecraft. The laminated shell was composed of an ablator, bond, 2 stainless steel face sheets, and a 2 inch thick stainless steel core. Thermal and mechanical loadings were considered. A structural model of the Apollo aft heat shield substructure was analyzed for a variety of thermal and mechanical loadings. A correlation was made of the analysis with test data and 2 independent digital computer analyses. An analysis of a hemisphere under hydrostatic loading was included to establish a link with "exact" theory. The development of the theory, transformations, Fortran programming effort, and substantiating data from the basis of the research. Selected stresses and displacements were used in comparisons to demonstrate the accuracy of the procedure.en
dc.format.extent209 leaves : illustrationsen
dc.rightsThis thesis was part of a retrospective digitization project authorized by the Texas A&M University Libraries. Copyright remains vested with the author(s). It is the user's responsibility to secure permission from the copyright holder(s) for re-use of the work beyond the provision of Fair Use.en
dc.subjectCivil Engineeringen
dc.titleStiffness matrix solution for shells of revolution possessing variable thickness heat protectionen
dc.typeThesisen Engineeringen A&M Universityen of Philosophyen
dc.contributor.committeeMemberHirsch, T. J.
dc.format.digitalOriginreformatted digitalen
dc.publisher.digitalTexas A&M University. Libraries

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