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• W2028837571 abstract "In this study, the instability of delaminated cross-ply thin laminated cylindrical shells and panels when subjected to supersonic flow parallel to its length edge is investigated. The delamination is parallel to the shell reference and it extends along the entire length of the cylindrical shell. The Love’s shell theory and Von-Karman–Donnell type of kinematic relations along with first-order potential theory have been employed to construct the aeroelastic equations of motion. The effects of several parameters such as length to radius ratio, delamination position, size and thickness on the critical values are discussed in the details. The results indicate that the presence of delamination reduced the overall stiffness of the structure and thereby decreases the flutter critical boundaries." @default.
• W2028837571 created "2016-06-24" @default.
• W2028837571 creator A5060315643 @default.
• W2028837571 date "2012-09-01" @default.
• W2028837571 modified "2023-09-24" @default.
• W2028837571 title "Flutter of delaminated cross-ply laminated cylindrical shells" @default.
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• W2028837571 doi "https://doi.org/10.1016/j.compstruct.2012.03.042" @default.
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