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| Optimal Design of Composite Wings of Light Aircraft Based on Response Surface Method |
| Received:November 20, 2024 Revised:March 16, 2025 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/issn.1672-9242.2025.04.008 |
| KeyWord:composites layer thickness laying sequence response surface method wings light aircraft |
| Author | Institution |
| LI Yuze |
Naval Equipment Department, Xi'an , China |
| YUAN Song |
Naval Equipment Department, Xi'an , China |
| LUO Jinshan |
Chongqing Changan Wangjiang Industrial Group Co., Ltd., Chongqing , China |
| LIU Changjiang |
Chongqing Changan Wangjiang Industrial Group Co., Ltd., Chongqing , China |
| TAN Peilin |
School of Materials Science and Engineering, Chongqing University of Technology, Chongqing , China |
| ZHOU Zhiming |
School of Materials Science and Engineering, Chongqing University of Technology, Chongqing , China |
| CHEN Quanlong |
The Green Aerotechnics Research Institute of Chongqing Jiaotong University, Chongqing , China |
| ZENG Xianjun |
The Green Aerotechnics Research Institute of Chongqing Jiaotong University, Chongqing , China |
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| Abstract: |
| The work aims to obtain a lightweight composite aircraft wing through optimizing the design of layer thickness and laying sequence of composites. With a light aircraft composite wing as the research object, CATIA software was used to build a composite wing structure model, and ANSYS finite element software was used to load constraints with mechanical properties as output variables to perform a sensitivity analysis on important parts of the wing. Then, with the maximum displacement deformation, stress limit and strain limit as response variables, and the minimum structural mass of the wing as the optimization objective, the laminate optimization design of the composite wing was carried out based on the response surface method. The research showed that layer thickness had a more significant effect on composite wing performance than layer sequence, and the skin thickness had the greatest impact on the mechanical properties of the wing. The weight of the alloy wing after optimization was reduced by 16%. Combining this optimization method with finite element analysis, the accuracy and reliability of the calculation results are high, which provides a reference for the optimization design of composites in aeronautical structures. |
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