A revised Ladevèze criteria for carbon fiber reinforced laminated plates
Cunxian Wang,
Chao Hang,
Tao Suo,
Yulong Li,
Pu Xue
Affiliations
Cunxian Wang
School of Aeronautics, Northwestern Polytechnical University, Xi'an, 710072, China
Chao Hang
Commercial Aircraft Corporation of China Ltd, Shanghai, 200126, China
Tao Suo
School of Aeronautics, Northwestern Polytechnical University, Xi'an, 710072, China; Fundamental Science on Aircraft Structural Mechanics and Strength Laboratory, Northwestern Polytechnical University, Xi'an, 710072, China; Corresponding author. School of Aeronautics, Northwestern Polytechnical University, Xi'an, 710072, China.
Yulong Li
School of Aeronautics, Northwestern Polytechnical University, Xi'an, 710072, China; Fundamental Science on Aircraft Structural Mechanics and Strength Laboratory, Northwestern Polytechnical University, Xi'an, 710072, China
Pu Xue
School of Aeronautics, Northwestern Polytechnical University, Xi'an, 710072, China; Fundamental Science on Aircraft Structural Mechanics and Strength Laboratory, Northwestern Polytechnical University, Xi'an, 710072, China
All parameters of revised Ladevèze failure criterion in Table 1 were determined based on mechanical tests which mainly include quasi-static tensile experiments, quasi-static compressive experiments, quasi-static tensile cyclic loading experiments, the dynamic tensile experiments, dynamic compressive experiments, quasi-static and dynamic inter-laminar shear experiments. The quasi-static experiments were performed using an electronic universal testing machine with a maximum load capacity of 10KN, and the split Hopkinson pressure bar (SHPB) and split Hopkinson tension bar (SHTB) were employed in dynamic experiments. In addition, the parameters of traditional orthogonal anisotropic model and cohesive layer for the laminated plates are listed in Table 2. Keywords: Ladevèze failure criterion, Quasi-static experiments, Dynamic experiments, Split Hopkinson bar
