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Analysis methods and preliminary design studyThe shuttle orbiter body flap was studied to define loads and temperatures and to assess various structural concepts. Laminated-structure analysis capability was required. An appraisal of the available structural analysis programs, NASTRAN and SPAR, indicates that neither had all the capabilities required. The thermal analysis program, MITAS solved the problem once a model was generated but model generation and verification was laborious and transfer of temperatures to the structural program usually required interpolation. Therefore it was decided to incorporate both capabilities in the SPAR finite element program.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Blackburn, C. L.
(Tennessee Univ. at Nashville Hampton, VA, United States)
Robinson, J. C.
(NASA Langley Research Center)
Date Acquired
August 9, 2013
Publication Date
August 1, 1979
Publication Information
Publication: Graphite/Polyimide Composites
Subject Category
Composite Materials
Accession Number
Distribution Limits
Work of the US Gov. Public Use Permitted.

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