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Stress analysis and damage evolution in individual plies of notched composite laminates subjected to in-plane loads

Chinese Journal of Aeronautics 2017年第1期30卷 447-460页

作者： Hu Junshan Zhang Kaifu Cheng Hui Liu Ping Zou Peng Song Danlong The Ministry of Education Key Lab of Contemporary Design and Integrated Manufacturing Technology Northwestern Polytechnical University Xi'an 710072 China School of Mechanical Engineering Northwestern Polytechnical University Xi'an 710072 China

This work aims to investigate local stress distribution, damage evolution and failure of notched composite laminates under in-plane loads. An analytic method containing uniformed boundary equations using a complex variable approach is developed to present layer-by-layer stresses around the notch. The uniformed boundary equations established in series together with conformal mapping functions are capable of dealing with irregular boundary issues around the notch and at infinity. Stress results are employed to evaluate the damage initiation and propagation of notched composites by progressive damage analysis（PDA）. A user-defined subroutine is developed in the finite element（FE） model based on coupling theories for mixed failure criteria and damage mechanics to efficiently investigate damage evolution as well as failure modes. Carbon/epoxy laminates with a stacking sequence of [45°/0°/ 60°/90°]sare used to investigate surface strains, in-plane load capacity and microstructure of failure zones to provide analytic and FE methods with strong validation. Good agreement is observed between the analytic method, the FE model and experiments in terms of the stress（strain） distributions, damage evaluation and ultimate strength, and the layerby-layer stress components vary according to a combination effect of fiber orientation and loading type, causing diverse failure modes in individuals.

关键词： Damage evolution Failure mode Failure strength Layer-by-layer stresses user-defined subroutine

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