Publikationsdatum:
2011-08-17
Beschreibung:
The 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.
Schlagwort(e):
COMPOSITE MATERIALS
Materialart:
Graphite/Polyimide Composites; p 303-318
Format:
text
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