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The compression after impact (CAI) strength of specially orthotropic composite laminates with up to 21 plies is presented, as analyzed by an existing strip model. Candidate layups are preselected to exhibit no coupling response, with manufacturing rules applied. These criteria, along with the use of a simple surrogate sublaminate buckling model, were chosen to allow analysis of all feasible laminates in the design space without excessive computation time. Results indicate that although the inclusion of non-symmetric layups in the design space does not give benefits with respect to maximum achievable damage tolerance, these laminates can exhibit damage tolerance close to that of a symmetric or antisymmetric design for some ply counts. It is also noted that in some instances increasing the number of plies in a laminate can actually reduce the highest achievable threshold load for damage tolerance, as a result of the large influence Poisson's ratio has on sublaminate buckling. Average errors in the surrogate model were low in all cases, with maximum non-conservative errors less than 1%. The surrogate buckling model reduced computational time by over 99% when compared to the fully exhaustive search.
|Title of host publication||Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference|
|Publisher||American Institute of Aeronautics and Astronautics|
|Publication status||Published - 2011|
|Event||52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference - Denver, USA United States|
Duration: 3 Apr 2011 → 6 Apr 2011
|Conference||52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference|
|Country/Territory||USA United States|
|Period||3/04/11 → 6/04/11|
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- 1 Finished
1/04/10 → 30/09/14
Project: Research council