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Fibrous orientation effects on the deformation and stress of a bird-like (pigeon) composite wing was studied. The bird wing is simulated and modeled by mechanical APDL software. The stress and displacement results of bird wing model under different laying modes are obtained by finite element method. The optimal laying mode is analyzed. The results are checked by strength theory in composite mechanics. The results show that for singe orientation [-20] 4  is the best orientation. For 4 layers structure, [-45/90/0/45] has best performance in 1st layer while [45/0/-45/90] has worst performance; [0/-45/90/45] has best performance in 2nd layer while [0/45/-45/90] has worst performance. [45/90/-45/0] has best performance for pigeon wing in this design in 3rd layer while [-45/0/90/45] has worst performance. [45/0/90/-45] has best performance for pigeon wing in this design in 4th layer while [-45/90/0/45] has worst performance. By comparison, it is found that the different-direction pavement is better than the same-direction pavement.

Fibrous Orientation Effects on the Deformation and Stress of a Pigeon-like Flapping-wing Micro Aerial Vehicle Based on APDL