| 李朋辉,王栋华,杨磊峰,彭星.蒙皮-翼肋连接对复材壁板压缩屈曲的影响研究[J].装备环境工程,2025,22(3):69-79. LI Penghui,WANG Donghua,YANG Leifeng,PENG Xing.Effects of Connection between Skin and Wing Rib on Compressional Properties of Composite Panels[J].Equipment Environmental Engineering,2025,22(3):69-79. |
| 蒙皮-翼肋连接对复材壁板压缩屈曲的影响研究 |
| Effects of Connection between Skin and Wing Rib on Compressional Properties of Composite Panels |
| 投稿时间：2025-02-19 修订日期：2025-03-08 |
| DOI：10.7643/issn.1672-9242.2025.03.009 |
| 中文关键词: 复合材料 整体壁板 翼肋 连接 屈曲 承载性能 有限元仿真中图分类号:V214.19 文献标志码:A 文章编号:1672-9242(2025)03-0069-11 |
| 英文关键词:composite integral stiffened panel wing rib connection buckling load-bearing performance finite element simulation |
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| 中文摘要: |
| 目的 研究蒙皮与翼肋连接与否对整体壁板的屈曲承载能力具体影响。方法 针对机翼结构中常见的蒙皮与翼肋连接和不连接两种构型，通过实物样件压缩试验分析、局部屈曲临界载荷理论分析、整体壁板在压缩载荷下的屈曲有限元仿真分析和3种结果对比分析，开展整体壁板屈曲承载能力的系统性研究。结果 蒙皮与翼肋连接、蒙皮与翼肋不连接2组试验件的平均屈曲载荷相差0.98%，蒙皮与翼肋连接或不连接对一阶曲模态下的屈曲载荷的影响很小。翼肋与蒙皮的连接对复合材料整体加筋壁板二阶和以上的屈曲模态有所影响，变化较大。蒙皮与翼肋连接、蒙皮与翼肋不连接两种构型对比下的有限元计算屈曲载荷、试验屈曲载荷均相差很小。同时2种构型各自的有限元计算屈曲载荷、试验屈曲载荷进行对比，相差也很小。结论 在机翼结构的工程设计中，对于非密封肋，在不考虑油箱密封等的连接下可简化翼肋与壁板的连接，从而减少结构质量，简化装配。复合材料机翼加筋壁板的工程设计边界通常为一阶屈曲，可认为翼肋与蒙皮的连接对复合材料机翼加筋壁板的屈曲模态不构成影响。整体壁板压缩试验的局部屈曲载荷计算方法、有限元分析方法和试验方法成熟度高，吻合性好。 |
| 英文摘要: |
| The work aims to study the specific effect of the connection or disconnection between the skin and wing ribs on the buckling load-carrying capacity of the integral panel. For the two common configurations of the wing structure, namely the connection and disconnection between the skin and wing ribs, a systematic study on the buckling load-carrying capacity of the integral panel was conducted through physical sample compression tests, theoretical analysis of local buckling critical loads, finite element simulation analysis of the integral panel under compressive loads, and comparison of the three results. The average buckling loads of the two groups of test specimens with and without the connection between the skin and wing ribs differed by 0.98%. The connection or disconnection between the skin and wing ribs had a negligible effect on the buckling load in the first-order bending mode. The connection between the wing ribs and skin had a significant impact on the second-order and higher buckling modes of the composite integral stiffened panel. Through finite element calculation, thebuckling loads and test buckling loads of the two configurations with and without the connection between the skin and wing ribs were close. At the same time, thebuckling loads and test buckling loads calculated by finite element of each configuration were also close. In the engineering design of wing structures, for non-sealing ribs, the connection between the wing ribs and the panel can be simplified without considering the connection for fuel tank sealing, thereby reducing the structural weight and simplifying the assembly. The engineering design boundary of the composite wing stiffened panel is usually the first-order buckling, and it can be considered that the connection between the wing ribs and the skin does not affect the buckling mode of the composite wing stiffened panel. The methods for calculating local buckling loads in integral panel compression tests, finite element analysis, and tests are mature and have good consistency. |
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