NDLI: Postbuckling behavior of graphite-epoxy panels

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Postbuckling behavior of graphite-epoxy panels

Content Provider	NASA Technical Reports Server (NTRS)
Author	Dickson, J. N. Rouse, M. Starnes Jr., J. H.
Copyright Year	1984
Description	Structurally 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.
File Size	21461127
Page Count	21
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19840021907
Archival Resource Key	ark:/13960/t9t19v76v
Language	English
Publisher Date	1984-08-01
Access Restriction	Open
Subject Keyword	Composite Materials Structural Design Panels Rigid Structures Failure Modes Compression Tests Compression Loads Aircraft Construction Materials Aircraft Design Thermosetting Resins Stress Distribution Shear Stress Graphite-epoxy Composites Fuselages Buckling Aircraft Structures Plates Impact Damage Loads Forces Structural Analysis Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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