复材层合板开口薄壁受压失稳及失效分析.pdfVIP

复材层合板开口薄壁受压失稳及失效分析.pdf

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复材层合板开口薄壁受压失稳及失效分析.pdf

Buckling and Failure of Compression-loaded Composite Laminated Shells with Cutouts * Mark W. Hilburger NASA Langley Research Center, Hamp ton Virginia 23681-2199 Results from a numerical and experimental study that illustrate the effects of laminate orthotropy on the buckling and failure response of compression-loaded composite cylindrical shells with a cutout are presented. The effects of orthotropy on the overall response of compression-loaded shells is described. In general, preliminary numerical results appear to accurately predict the buckling and failure characteristics of the shell considered herein. In particular, some of the shells exhibit stable post-local-buckling behavior accompanied by interlaminar material failures near the free edges of the cutout. In contrast another shell with a different laminate stacking sequence appears to exhibit catastrophic interlaminar material failure at the onset of local buckling near the cutout and this behavior correlates well with corresponding experimental results. I. Introduction Thin-walled shell structures are a fundamental component found in aircraft, spacecraft, and launch vehicles. In many applications, these structural components contain cutouts or openings that serve as doors, windows, or access ports, or are used to reduce weight. Often, some type of reinforcement is used around a cutout to eliminate local deformations and stress c

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