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Secondary buckling of compression-loaded composite plates
A stiffened plate subjected to an inplane compressive load buckles when this load exceeds a critical value. For loads exceeding this critical value by several factors, and for certain laminates, boundary conditions, and geometric and stiffener parameters, the plate suddenly changes it shape. This phenomenon is due to the existence of a bifurcation point on the postbuckling load-deflection path and is known as secondary buckling. For the clamped-simply supported square plate, the postbuckling out-of-plane deflection before snapping consists of one half wave in both x and y directions. After secondary buckling, the out-of-plane deflection consists of two half waves in the x direction and one half wave in the y direction. The present work is focussed on understanding the parameters which govern secondary buckling behavior. The paper describes in more detail the phenomenon of secondary buckling and illustrates the sensitivity of such a phenomenon to key material and geometric parameters of the problem. The finite element method is used. The condition for secondary buckling is determined by examining the eigenvectors of the local tangent stiffness matrix. When the lowest eigenvalue of this matrix is sufficiently close to zero, the corresponding eigenvector is used as a perturbation to move the solution to the secondary configuration.
Secondary buckling of compression-loaded composite plates
A stiffened plate subjected to an inplane compressive load buckles when this load exceeds a critical value. For loads exceeding this critical value by several factors, and for certain laminates, boundary conditions, and geometric and stiffener parameters, the plate suddenly changes it shape. This phenomenon is due to the existence of a bifurcation point on the postbuckling load-deflection path and is known as secondary buckling. For the clamped-simply supported square plate, the postbuckling out-of-plane deflection before snapping consists of one half wave in both x and y directions. After secondary buckling, the out-of-plane deflection consists of two half waves in the x direction and one half wave in the y direction. The present work is focussed on understanding the parameters which govern secondary buckling behavior. The paper describes in more detail the phenomenon of secondary buckling and illustrates the sensitivity of such a phenomenon to key material and geometric parameters of the problem. The finite element method is used. The condition for secondary buckling is determined by examining the eigenvectors of the local tangent stiffness matrix. When the lowest eigenvalue of this matrix is sufficiently close to zero, the corresponding eigenvector is used as a perturbation to move the solution to the secondary configuration.
Secondary buckling of compression-loaded composite plates
Sekundärbeulen von druckbelasteten Verbundplatten
Tiwari, N. (author) / Hyer, M.W. (author)
1996
9 Seiten, 11 Bilder, 1 Tabelle, 18 Quellen
Conference paper
English
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