摘要
参照国标设计了碳纤维层合板冲击试验试件,并采用湿法常温真空加压固化工艺制作。选取不同冲击能量对试件冲击。建立了碳纤维层合板非线性损伤有限元模型:编写用户子程序定义层合板的损伤。选用基于应变的Chang-Chang准则判定纤维和基体损伤。使用二次应力准则判定胶层单元的初始损伤;采用BK准则判定胶层单元的失效。结果表明:冲击头接触力合力峰值随冲击能量增大呈先增大后减小;冲击头最大位移和能量损耗率随冲击能量增大呈单调上升趋势。试件受冲击后先出现基体拉伸损伤,并由冲击区域沿纤维方向延展;低能量组试件的基体拉伸损伤面积随冲击能量增大呈线性增大,高能量组呈非线性增大;分层损伤主要集中在冲击区域;分层面积随冲击能量增大呈线性增大;接触力合力峰值的最大计算误差为18.51%。数值计算损伤状态与试件实际损伤形貌基本吻合。
The carbon fiber impact test specimen was designed with reference to the national experiment standard.The specimens were manufactured by the wet layup method and the vacuum pressure curing process at room temperature.The impact test of the specimens was carried out with different typical impact energies.A nonlinear damage finite element model of the carbon fiber laminates was established.The user subroutine was programmed to define the damage of the laminates.The strain-based Chang-Chang criterion was used to determine the damage of fiber and matrix.The quadratic stress criterion was used to determine the initial damage of the cohesive element.The BK criterion was used to determine the entire failure of the cohesive element.The nonlinear damage process of the laminates under impact loading was analyzed.It is showed that the peak value of the resultant contact force of the impact head first increases and then decreases with the increase of the impact energy.The maximum displacement of the impact head and the energy dissipation rate show a monotonous upward trend with the increase of impact energy.Under impact loading,the tensile damage of the matrix occurs first,and extends along the fiber direction.The matrix tensile damage area of the low impact energy specimens increases linearly with the increase of impact energy,and nonlinear trend is observed for high impact energy specimens.The delamination damage is mainly concentrated in the impact domain.The delamination area increases with the increase of impact energy.The maximum calculation error of the contact force peak value is about 18.51%.The damage status of the specimens given by the numerical analysis is consistent with the actual damage configuration.
作者
刘峰
张梦涛
王卓煜
LIU Feng;ZHANG Mengtao;WANG Zhuoyu(Civil Aviation Flight University of China,Guanghan 618307,China)
出处
《兵器装备工程学报》
CAS
CSCD
北大核心
2022年第11期16-24,共9页
Journal of Ordnance Equipment Engineering
基金
民航局科技创新引导资金项目(14002600100017J171)
中国民用航空飞行学院大学生创新项目(S202010624108)。
关键词
碳纤维
层合板
冲击
非线性
损伤
carbon fiber
laminates
impact
nonlinear
damage
