Mechanical Performance of Composite Laminate with Oblique Splicing Ply
In order to cognition the mechanical performance of the composite laminate structures with ply splicing, the specific carbon/polyurethane composite laminate specimens has been designed to determine this material mechanical properties by means of the tension testing. The tensile elastic modulus and tensile strength are measured in the experiment. The breakage happened in place of splicing along the splicing line. The oblique ply splicing significantly influence the stiffness of the composite laminate, but the strength of the composite laminate with splicing ply is mainly determined by the continuous layers. The laminate fails in low load value. The numerical analyses using linear elastic and progressive damage approaches were conducted with the commercial FEM software (ABAQUS). The linear elastic finite element model is established to calculate the interlaminar stress of ply splicing in different layers angles. The progressive model, based on the damage mechanisms observed at the ply level and hypotheses regarding their effect on material stiffness, is used to predict the strength by means of numerical computatioa There are three different criteria used here in the prediction. By combining the damage model with classical lamination theory, the behavior of laminates under plane stress loading is predicted. The capabilities of the proposed damage model are assessed based on comparison to experimental data.
composite laminate ply splicing tension strength FEM
Li Liang Jia Purong Jiao Guiqiong
Department of Engineering Mechanics , Northwestern Polytechnical University, Xian 710129,China Department of Engineering Mechanics , Northwestern Polytechnical University, Xian 710129, China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
856-859
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）