| 李禹泽,袁嵩,罗金山,刘长江,谭培林,周志明,陈全龙,曾宪君.基于响应面法的轻型飞机复合材料机翼优化设计[J].装备环境工程,2025,22(4):59-66. LI Yuze,YUAN Song,LUO Jinshan,LIU Changjiang,TAN Peilin,ZHOU Zhiming,CHEN Quanlong,ZENG Xianjun.Optimal Design of Composite Wings of Light Aircraft Based on Response Surface Method[J].Equipment Environmental Engineering,2025,22(4):59-66. |
| 基于响应面法的轻型飞机复合材料机翼优化设计 |
| Optimal Design of Composite Wings of Light Aircraft Based on Response Surface Method |
| 投稿时间：2024-11-20 修订日期：2025-03-16 |
| DOI：10.7643/issn.1672-9242.2025.04.008 |
| 中文关键词: 复合材料 铺层厚度 铺层顺序 响应面法 机翼 轻型飞机中图分类号:TH122 文献标志码:A 文章编号:1672-9242(2025)04-0059-08 |
| 英文关键词:composites layer thickness laying sequence response surface method wings light aircraft |
| 基金项目:重庆市技术创新与应用产业类重点项目(cstc2021ycjh-bgzxm0284，CSTB2022TIAD-DEX0019，2022TIAD-DEX0040)；重庆市教委重大科研项目(KJZD-M202401104)；绍兴英才项目(2022SXRC)；重庆理工大学科研项目(2023TBZ019，2024TBA025) |
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| Author | Institution |
| LI Yuze | Naval Equipment Department, Xi'an 710025, China |
| YUAN Song | Naval Equipment Department, Xi'an 710025, China |
| LUO Jinshan | Chongqing Changan Wangjiang Industrial Group Co., Ltd., Chongqing 401120, China |
| LIU Changjiang | Chongqing Changan Wangjiang Industrial Group Co., Ltd., Chongqing 401120, China |
| TAN Peilin | School of Materials Science and Engineering, Chongqing University of Technology, Chongqing 400054, China |
| ZHOU Zhiming | School of Materials Science and Engineering, Chongqing University of Technology, Chongqing 400054, China |
| CHEN Quanlong | The Green Aerotechnics Research Institute of Chongqing Jiaotong University, Chongqing 400050, China |
| ZENG Xianjun | The Green Aerotechnics Research Institute of Chongqing Jiaotong University, Chongqing 400050, China |
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| 中文摘要: |
| 目的 通过对复合材料铺层厚度和铺层顺序的优化设计，获得轻量化的轻型飞机复合材料机翼。方法 以一种轻型飞机复合材料机翼为研究对象，利用CATIA软件构建复合材料机翼结构模型，通过ANSYS有限元软件进行约束条件加载，将力学性能作为输出变量，对机翼重要零部件进行灵敏度分析。然后以机翼结构质量最小作为优化目标，将最大位移变形、应力极限和应变极限作为响应变量，基于响应面法对复合材料机翼进行铺层优化设计。结果 铺层厚度相较于铺层顺序对复合材料机翼性能的影响更为显著，其中蒙皮厚度对机翼力学性能影响最大。与优化前相比，优化后机翼质量减少16%。结论 优化方法与有限元分析相结合，计算结果的精度和可靠度较高，为复合材料在航空结构的优化设计提供了参考。 |
| 英文摘要: |
| 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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