NDLI: Minimum-mass design of filamentary composite panels under combined loads: design procedure based on a rigorous buckling analysis

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Minimum-mass design of filamentary composite panels under combined loads: design procedure based on a rigorous buckling analysis

Content Provider	NASA Technical Reports Server (NTRS)
Author	Anderson, M. S. Agranoff, N. Stroud, W. J.
Copyright Year	1977
Description	A procedure is presented for designing uniaxially stiffened panels made of composite material and subjected to combined inplane loads. The procedure uses a rigorous buckling analysis and nonlinear mathematical programing techniques. Design studies carried out with the procedure consider hat-stiffened and corrugated panels made of graphite-epoxy material. Combined longitudinal compression and shear and combined longitudinal and transverse compression are the loadings used in the studies. The capability to tailor the buckling response of a panel is also explored. Finally, the adequacy of another, simpler, analysis-design procedure is examined.
File Size	2101947
Page Count	43
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19770021580
Archival Resource Key	ark:/13960/t4gn30j41
Language	English
Publisher Date	1977-07-01
Access Restriction	Open
Subject Keyword	Structural Mechanics Shear Properties Composite Materials Mathematical Models Computerized Simulation Design Analysis Buckling Loads Forces Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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