摘要
通过有限元方法和渐进损伤模拟方法对复材泡沫夹芯结构受低能冲击的损伤过程和损伤特性进行仿真预测。给出了四种不同面板厚度及泡沫夹芯厚度夹芯结构在既定失效准则下的损伤演化和渐进扩展过程,给出了冲击能量与损伤类型及损伤程度的关系、冲击能量与最大载荷、损伤面积、凹坑深度等规律性结论,并对比简支和固支两种边界条件的影响。仿真结果与两种规格复材泡沫夹芯结构的试验结果进行了对比分析,对比结果表明:仿真数据与相对应的试验数据较为吻合,证实了本仿真方法对泡沫夹芯结构在低能量冲击条件下损伤过程模拟的有效性;随着冲击能力的提高,被冲击结构的所承受的最大载荷、最大冲头速度、凹坑深度相应提高,但冲头的零速度时间差异不大;在简支与固支边界条件下,被冲击结构所承受的最大载荷、零速度时间差异不大,但凹坑深度相差较大,反映出不同支持条件对被冲击结构能量吸收的影响。
The process and characters of impact damage in the composite-foam sandwich structure was simulated for four kinds of foam sandwich structure with different thickness panel based on the FEM,specific failure criteria and progressive failure method.The relationship between impact energy and damage types,damage grade,the maximum impact loads,damage area, dent depth was provided under condition of simple supporting and fixed supporting BCs.Comparison between simulation results and test results for two configuration of sandwich was provided and the results shown that the simulation "data match with the test data well,which verified the efficiency of the current method.Along with the improvement of the impact energy,the impact loads,maximum speed,dent depth in the impacted structure increases,but the times of 0speed of the impact head shown tittle difference.The BCs of simple support or fixed support has no significant effect on the maximum impact load and time of 0speed of the head,however the dent depth differs much,which shows the different energy absorption of different supporting conditions.
作者
廉伟
王明义
吕军
LIAN Wei;WANG Mingyi;LV Jun(Commercial Aircraft Corporation of China Ltd.Shanghai Aircraft Design and Research Institute,Shanghai 201210)
出处
《纤维复合材料》
CAS
2018年第2期20-26,共7页
Fiber Composites
关键词
复合材料
泡沫
夹芯结构
冲击损伤
仿真
composite
foam
sandwich structure
impact damage
simulation