Damage characterization of the CFRP fan blade subjected to bird-strike impacts
This paper numerically investigated a bird-strike impact on a composite fan blade. A numerical model with a stabilized contact algorithm was presented to address the impact-induced contact based on the Lagrange multiplier method. The proposed method enables solving soft-body impact at high velocity, such as bird strike, without causing severe numerical instabilities. With the numerical model, we discussed the deformation and damage characteristics of a unidirectional composite plate induced by a bird-strike impact. As the impact velocity increases, the damage in the composite changes from bending-induced matrix-cracking to local shear perforation. The simulated results reveal that the transition velocity as a ballistic limit lies between 100 m/s and 150 m/s.
Polymer-matriz composites (PMCs) Fracture Impact behavior Computational modeling Finite element analysis (FEA)
Kei HEMMI Masaaki NISHIKAWA Nobuo TAKEDA
Department of Aeronautics and Astronautics, The University of Tokyo, Kashiwa, 277-8561, Japan Department of Advanced Energy, The University of Tokyo, Kashiwa, 277-8561, Japan
国际会议
北京
英文
1-4
2008-10-23（万方平台首次上网日期，不代表论文的发表时间）