@article{PIAN2026, 
author = {Rong PIAN and Fan YANG and Ling ZHANG and Fengrui LIU and Linjuan WANG and Libin ZHAO},
title = {Failure mode of composite laminated plates under compression-shear loading},
year = {2026},
journal = {Journal of Beijing University of Aeronautics and Astronautics},
volume = {52},
number = {4},
pages = {1254-1260},
keywords = {composite laminated plate, failure analysis, buckling, first-ply failure, compression-shear loading},
url = {https://www.sciopen.com/article/10.13700/j.bh.1001-5965.2024.0084},
doi = {10.13700/j.bh.1001-5965.2024.0084},
abstract = {Under compressive and shear pressures, composite laminates, which are crucial load-bearing components in airplanes, are vulnerable to buckling or overstress failure. In this paper, the theoretical analysis methods for buckling and first-ply-failure were adopted to predict the failure of composite laminated plates. The investigation was carried out on graphite/epoxy plates, with different load ratios, side length ratios, side length-thickness ratios, and lay-up angles. Two failure categories’ occurrence sequence as well as the failure loads’ variance were found. It is revealed that buckling and first-ply-failure occur in different orders under various load ratios. The load ratio ranges corresponding to buckling and first-ply-failure are affected by the side length ratio, side length-thickness ratio, and lay-up angle of the plate. The buckling mode is primarily influenced by the load ratio, side length ratio and lay-up angle, while the first-layer-failure mode is mainly affected by the load ratio and lay-up angle.}
}