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<p>The theoretical determination of critical buckling stress σ<sub><i>cr</i></sub> of a monocoque composite shell is based on an eigenvalue solution. This largely overpredicts the case of asymmetric buckling mode (circumferential waves around the shell exist or <i>n</i> ≠ 0) compared to the reported test data. Such shells need post-bucking analysis following a well-known SPLA approach or introducing an imperfection to obtain the knockdown factor for the design. The present study obtains an extended simple analytical solution to choose the right equation for the σ<sub><i>cr</i></sub> to predict different buckling modes. It is observed that the knockdown factor for the symmetric mode of buckling (<i>n</i> = 0) is nearly one. Once the monocoque shell with asymmetric buckling mode is considered a sandwich shell (with enhanced σ<sub><i>cr</i></sub>), the knockdown factor increases, making both linear and nonlinear values of σ<sub><i>cr</i></sub> nearly the same. This is because the lateral support of the rigid or semi-flexible honeycomb core makes imperfections insensitive to buckling. Sandwich option, even with a very small core height, allows the fiber stress to reach the material strength. No post-buckling regime analysis is required for the core shear buckling mode.</p>

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Demystification on Post-Buckling of Sandwich Shells

  • 期刊论文

  • 发表日期：

    2025年5月1日

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  • J. Vibin,
  • R. Ramesh Kumar,
  • S. Nagarajan,
  • S. Sunil Kumar

摘要

The theoretical determination of critical buckling stress σcr of a monocoque composite shell is based on an eigenvalue solution. This largely overpredicts the case of asymmetric buckling mode (circumferential waves around the shell exist or n ≠ 0) compared to the reported test data. Such shells need post-bucking analysis following a well-known SPLA approach or introducing an imperfection to obtain the knockdown factor for the design. The present study obtains an extended simple analytical solution to choose the right equation for the σcr to predict different buckling modes. It is observed that the knockdown factor for the symmetric mode of buckling (n = 0) is nearly one. Once the monocoque shell with asymmetric buckling mode is considered a sandwich shell (with enhanced σcr), the knockdown factor increases, making both linear and nonlinear values of σcr nearly the same. This is because the lateral support of the rigid or semi-flexible honeycomb core makes imperfections insensitive to buckling. Sandwich option, even with a very small core height, allows the fiber stress to reach the material strength. No post-buckling regime analysis is required for the core shear buckling mode.