Optimization Design of Large Scale Wing Size via Refined Finite Element Model
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摘要: 在虚拟试验构建的精细有限元模型基础上，开展了大型机翼尺寸优化设计技术的研究。通过对不同工况模型中的载荷进行转换，构建了统一的优化模型；采用翼梁、翼肋的站位，将机翼主翼盒自动划分为不同的设计区域，并根据每个设计区域特点定义了优化变量和设计约束。利用满应力优化算法对机翼进行了尺寸优化设计，达到13.3%的减重效果。算例表明，利用精细有限元模型进行尺寸优化的方案是可行的，由此产生的优化模型构建问题可通过相关模型处理技术得以解决。Abstract: Based on the refined finite element model constructed by using the virtual test, the study on the optimization design of large scale wing is carried out. A unified optimization model is constructed by transforming the loads of different working condition models. Using the spar and rib positions, the main wing box is automatically divided into the different design regions, and the optimization variables and design constraints are defined according to the characteristics of each design region. The wing size is optimized by using the full stress optimization algorithm to achieve a weight reduction rate of 13.3%. A numerical example shows that the optimization of the wing size by using the refined finite element model is feasible, and the modeling problems can be solved by dealing the related model.
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Key words:
- wing /
- refined finite element model /
- size optimization /
- virtual test
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表 1 部分优化变量
部位 变量名称 初值/mm 下限值/mm 上限值/mm 梁腹板
厚度V1040 2.5 1.25 3.75 V1041 2.5 1.25 3.75 翼肋腹板
厚度V1081 2.5 1.25 3.75 V1082 2.5 1.25 3.75 蒙皮厚度 V1101 3.3 1.65 4.95 V1102 3.3 1.65 4.95 V1103 3 1.5 4.5 V1104 3 1.5 4.5 
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