## Abstract

An elasticity theory based approach is developed for delamination buckling of simply-supported composite laminates whose behavior is referred to as cylindrical bending. The approach assures an accurate description of the transverse shear and the transverse normal effects in delamination buckling of composite plates. The uniform prebuckling stress assumption, which is equivalent to the membrane assumption used in plate theories, is made for deriving the elasticity theory based buckling equations. The closed-form expressions for the displacements and stresses are derived and the nonlinear eigenvalue equations are presented which are used to solve for critical loads. The results obtained from the elasticity solution are compared with the critical loads furnished by the existing classical laminate theory and a previously developed higher-order shear deformation theory. The solution provides a means of accurate assessment of existing two-dimensional plate theories.

Original language | English (US) |
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Title of host publication | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |

Publisher | AIAA |

Pages | 2543-2551 |

Number of pages | 9 |

Volume | 4 |

State | Published - 1996 |

Event | Proceedings of the 1996 37th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Part 4 (of 4) - Salt Lake City, UT, USA Duration: Apr 15 1996 → Apr 17 1996 |

### Other

Other | Proceedings of the 1996 37th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Part 4 (of 4) |
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City | Salt Lake City, UT, USA |

Period | 4/15/96 → 4/17/96 |

## ASJC Scopus subject areas

- Architecture