A nonlocal damage theory for laminated plate with application to aircraft damage tolerance
Design of commercial aircraft structure, composed of composite material, requires the prediction of failure loads given large scale damage. In particular, a fuselage of graphite/epoxy lamination was analyzed for damage tolerance given a standard large crack that severed both skin and internal struct...
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| Language: | en_US |
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2012
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| Online Access: | http://hdl.handle.net/1957/34015 |