复合材料泡沫夹芯结构低速冲击损伤研究  

Low-velocity Impact Damage Analysis on Composites Foam Core Sandwich Structure

作　　者：夏龙[1] 徐绯[1] 李巧[2] 姚雄华[2] 

机构地区：[1]西北工业大学航空学院,西安710072 [2]中国航空工业集团公司第一飞机设计研究院,西安710089

出　　处：《航空工程进展》2011年第4期425-431,共7页Advances in Aeronautical Science and Engineering

基　　金：教育部新世纪优秀人才支持计划(NCET080454)

摘　　要：随着复合材料夹芯结构在航空领域的广泛应用,对其抗冲击性能的研究变得越来越重要。本文对泡沫夹芯结构的低速冲击问题采用试验及数值分析的手段进行研究,比较了不同冲击能量下泡沫夹芯结构的冲击响应特点,并利用数值分析手段揭示了冲击损伤的破坏机理,同时计算得到了该夹芯结构的临界冲击能量,模拟结果与试验吻合较好,可为工程设计提供一定的参考;同时对比分析了全模型与1/4模型、衰减参数、衰减次数对冲击响应分析结果的影响。结果表明:采用1/4模型,考虑泊松比的参数衰减以及50次退化方式能够提高数值模拟的计算效率和精度。The mechanical properties of sandwich composites become more and more important as a result of the wide field application of the sandwich composites. Firstly, both experimental test and numerical computation are used to analyze the performance of sandwich composites in low-velocity impact. The dynamic responses of sand- wich composites are observed under different impact energies. The damage mechanism is figured out and the critical energy is obtained by the numerical computation method. Simulation result and experiment agree well. It can provide certain reference for engineering design. The influence of the whole model and the quarter model, the reduced parameters, reduced frequency to impact response analysis are researched. The results show that u- sing the method of quarter model, reduced parameters considered with Poisson ratio, 50 times reduced frequency can improve the efficiency and precision of numerical simulation.

关 键 词：泡沫夹芯结构 低速冲击 损伤 

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]