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Postbuckling behavior of graphite-epoxy panelsStructurally efficient fuselage panels are often designed to allow buckling to occur at applied loads below ultimate. Interest in applying graphite-epoxy materials to fuselage primary structure led to several studies of the post-buckling behavior of graphite-epoxy structural components. Studies of the postbuckling behavior of flat and curved, unstiffened and stiffened graphite-epoxy panels loaded in compression and shear were summarized. The response and failure characteristics of specimens studied experimentally were described, and analytical and experimental results were compared. The specimens tested in the studies described were fabricated from commercially available 0.005-inch-thick unidirectional graphite-fiber tapes preimpregnated with 350 F cure thermosetting epoxy resins.
Document ID
19840021907
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Starnes, J. H., Jr. (NASA Langley Research Center Hampton, VA, United States)
Dickson, J. N. (Lockheed-Georgia Co. Hampton, VA, United States)
Rouse, M. (NASA Langley Research Center)
Date Acquired
August 12, 2013
Publication Date
August 1, 1984
Publication Information
Publication: ACEE Composite Struct. Technol.
Subject Category
Composite Materials
Accession Number
84N29976
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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