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复合材料面板全高度蜂窝翼面结构分析
万爽1, 解海鸥1, 张涛1, 崔深山1, 仝凌云2
1.中国运载火箭技术研究院 研究发展中心,北京 100076;2.航天材料及工艺研究所,北京 100076
摘要:
针对复合材料面板全高度蜂窝夹层翼面结构,基于MSC.Patran/Nastran创建了翼面有限元模型,对均布载荷作用下的结构进行了仿真分析。结果表明:翼面结构最大位移2.79 mm,曲屈载荷33.7 kN。工程方法计算得到翼面结构曲屈应变1 308.6 με。静强度试验中实测翼面最大位移2.81 mm。理论与试验相结合的方式分析夹层翼面结构,最大位移值偏差约0.7%,证明了仿真分析模型的合理性,为该类型结构的工程应用提供了一定的参考。
关键词:  全高度蜂窝  翼面  研制  仿真分析  试验验证
DOI:10.12044/j.issn.1007-2330.2019.01.006
分类号:
基金项目:
Structure of Full Height Composite Honeycomb Wing
WAN Shuang1, XIE Haiou1, ZHANG Tao1, CUI Shenshan1, TONG Lingyun2
1.China Academy of Launch Vehicle Technology,Beijing 100076;2.Aerospace Research Institute of Materials & Processing Technology,Beijing 100076
Abstract:
For the full-height honeycomb sandwich airfoil of composite panel,the finite element model of the airfoil was created based on MSC.Patran/Nastran.The structure under uniform load was simulated and analyzed.The results show that maximum displacement of the structure is 2.79 mm,and the flexural load is 33.7 kN.At the same time,the structural flexural strain 1 308.6 με is calculated by engineering method.The maximum displacement of the measured airfoil in the static strength test is 2.81 mm. The theoretical and experimental methods are combined to analyze the airfoil of the sandwich structure.The maximum displacement value deviation is about 0.7%,which proves the rationality of the simulation analysis model and provides a reference for the engineering application of this type of structure.
Key words:  Full height honeycomb  Wing  Manufacture  Simulation analysis  Verify