聚碳酸脂本构方程及其在鸟撞风挡仿真中的应用  

Constitutive Equation of Polycarbonate and Its Application to Simulation of Windshield Under Bird Impact

作　　者：韩强[1] 于鹏[1] 姚小虎[1] 臧曙光[2] 李志强[3] 

机构地区：[1]华南理工大学土木与交通学院,广东广州510640 [2]中国建筑材料检验认证中心有限公司,北京100024 [3]太原理工大学应用力学与生物医学工程研究所,山西太原030024

出　　处：《华南理工大学学报（自然科学版）》2013年第8期99-102,共4页Journal of South China University of Technology(Natural Science Edition)

基　　金：国家自然科学基金资助项目(11072166);国家国际科技合作专项(2011DFA53080);山西省高等学校优秀青年学术带头项目

摘　　要：基于室温下的Instron静态压缩试验和霍普金森压杆(SHPB)动态试验,利用Johnson-Cook本构模型,并采用参数识别法和最小二乘法拟合相应的本构参数,确定了适合于聚碳酸脂的动态本构方程.发现低应变率下,理论值与实验值吻合较好;高应变率下,理论值与实验值的屈服点吻合较好.将其用于描述飞机风挡材料,应用非线性有限元程序LS-DYNA3D进行了鸟体撞击风挡的数值仿真计算.由风挡和鸟体的变形过程以及风挡的位移时程曲线可知,实验结果和数值结果吻合较好.Based on the dynamic experiment of split-Hopkinson pressure bar （SHPB） and the static compression experiment of Instron at the room temperature,a dynamic Johnson-Cook constitutive equation of polycarbonate is proposed by using the least square and parameter identification methods to fit the corresponding constitutive parameters.It is found that the theoretical values accord well with the experimental ones at lower strain rates while they accord well with each other only at yield points at higher strain rates.In addition,the model is employed to simulate the aircraft windshield under bird impact by using the nonlinear finite element software LS-DYNA3D.The results show that the deformations of the bird and the windshield as well as the history curve of the windshield displacement in the simulation accords well with those in the experiments.

关 键 词：聚碳酸脂 本构模型 应变率 风挡 

分 类 号：O344.3[理学—固体力学]