复合材料层板固化全过程残余应变/应力的数值模拟  

Numerical Simulation of Residual Strain/Stress for Composite Laminate during Overall Curing Process

作　　者：胡照会[1] 王荣国[1] 赫晓东[1] 杜善义[1] 

机构地区：[1]哈尔滨工业大学复合材料与结构研究所,哈尔滨150001

出　　处：《航空材料学报》2008年第2期55-59,共5页Journal of Aeronautical Materials

基　　金：国家863项目(2005AA304010)

摘　　要：采用商业软件对带有铝板的复合材料层板固化全过程残余应变/应力进行数值模拟计算。在固化过程的模拟中,应用有限元法计算复合材料层板热-化学模型,有限差分法计算固化动力学模型,通过设置较小的时间步实现求解两个模型强耦合的关系。在残余应力数值模拟中,化学收缩引起的应变在每一计算步以初始应变施加在复合材料结构上。基于以上技术,对带有铝合金的复合材料层板固化全过程残余应变/应力演化进行数值模拟,并分析纤维方向和垂直纤维方向复合材料的残余应变/应力演化历程。通过与试验中层板曲率的比较,验证文中模型计算的准确性。The process induced residual strain/stress of composite laminated plate with aluminum plate was numerically simulated by commerce software. Finite element analysis was used to simulate thermal-chemical model of composites laminated plate, and finite difference method was employed to calculate its cure kinetics model during curing process. The strong coupled relation between cure kinetics model and thermal-chemical model was expected to consider by setting minionum time step in finite difference method. Chemical shrinkage was applied to composite materials as an initial strain for each time increment in residual stress simulation residual strain/ stress of composite laminated plate with aluminum plate was successfully simulated on the basis of the mentioned technology. Moreover, history of residual strain/stress at along fiber orientation and vertical fiber orientation of composite material were analyzed. Compared to deflection of laminate in test, the validity of the results calculated by model was proved.

关 键 词：残余应变/应力 耦合 初始应变 约束 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]