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Effects of Defects on the Buckling Load of Rodpack Laminates

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The composite rod has emerged as a new material form that is currently being considered in the design of stiffener reinforced structures for low‐cost composite wing and fuselage structural applications. This paper covers buckling analysis of rodpack laminates with and without defects. Defects considered in this study include rods broken in the center, rods snlit vertically as well as horizontally in the rod layer, and delamination occurring at the interface between rod layer and unidirectional lamina. A fully three‐dimensional finite element analysis was conducted to investigate the effect of the critical buckling load due to these defects. A closed‐form expression of the bending stiffness for the rodpack laminates was also derived. This expression provides better accuracy for evaluating the column buckling for this laminate. The results indicate that vertical split or broken rods in the rodnack laminates do not affect the bucklinee load. However, for laminate with a horizontal solit rod the prediction of the critical buckling load has reduced about 8.7% compared with the laminate without damage.

Document Type: Research Article


Affiliations: Da Yeh University, Taiwan

Publication date: 2000-07-01

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  • The Journal of the American Helicopter Society is the world's only scientific journal dedicated to vertical flight technology. It is a peer-reviewed technical journal published quarterly by AHS International and presents innovative papers covering the state-of-the-art in all disciplines of rotorcraft design, research and development. (Please note that AHS members receive significant discounts on articles and subscriptions.)

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