Multiaxial fatigue life prediction of composite materials  

作　　者：Jingmeng WENG Weidong WEN Hongjian ZHANG 

机构地区：[1]Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing 210016, China [2]State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing 210016, China [3]College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

出　　处：《Chinese Journal of Aeronautics》2017年第3期1012-1020,共9页中国航空学报（英文版）

基　　金：the supports from the Jiangsu Province Key Laboratory of Aerospace Power System of China(No.NJ20140019);the National Natural Science Foundation of China(No.51205190)

摘　　要：In order to analyze the stress and strain fields in the fibers and the matrix in composite materials,a fiber-scale unit cell model is established and the corresponding periodical boundary conditions are introduced.Assuming matrix cracking as the failure mode of composite materials,an energy-based fatigue damage parameter and a multiaxial fatigue life prediction method are established.This method only needs the material properties of the fibers and the matrix to be known.After the relationship between the fatigue damage parameter and the fatigue life under any arbitrary test condition is established,the multiaxial fatigue life under any other load condition can be predicted.The proposed method has been verified using two different kinds of load forms.One is unidirectional laminates subjected to cyclic off-axis loading,and the other is filament wound composites subjected to cyclic tension-torsion loading.The fatigue lives predicted using the proposed model are in good agreements with the experimental results for both kinds of load forms.In order to analyze the stress and strain fields in the fibers and the matrix in composite materials,a fiber-scale unit cell model is established and the corresponding periodical boundary conditions are introduced.Assuming matrix cracking as the failure mode of composite materials,an energy-based fatigue damage parameter and a multiaxial fatigue life prediction method are established.This method only needs the material properties of the fibers and the matrix to be known.After the relationship between the fatigue damage parameter and the fatigue life under any arbitrary test condition is established,the multiaxial fatigue life under any other load condition can be predicted.The proposed method has been verified using two different kinds of load forms.One is unidirectional laminates subjected to cyclic off-axis loading,and the other is filament wound composites subjected to cyclic tension-torsion loading.The fatigue lives predicted using the proposed model are in good agreements with the experimental results for both kinds of load forms.

关 键 词：Fatigue damage parameter Finite element analysis Life prediction Multiaxial fatigue Periodical boundary condition 

分 类 号：V215.5[航空宇航科学与技术—航空宇航推进理论与工程]