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| Effects of Connection between Skin and Wing Rib on Compressional Properties of Composite Panels |
| Received:February 19, 2025 Revised:March 08, 2025 |
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| DOI：10.7643/issn.1672-9242.2025.03.009 |
| KeyWord:composite integral stiffened panel wing rib connection buckling load-bearing performance finite element simulation |
| Author | Institution |
| LI Penghui |
Unit 93170 of the PLA, Xi'an , China |
| WANG Donghua |
Unit 93170 of the PLA, Xi'an , China |
| YANG Leifeng |
Xi'an Aircraft Institute, Aviation Industry Corporation of China, Xi'an , China |
| PENG Xing |
Southwest Technology and Engineering Research Institute, Chongqing , China |
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| Abstract: |
| 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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