Optimization design of composite wing skin with honeycomb sandwich by genetic algorithm

DING Ling; SUN Hui; JIA Hong-guang; YANG Hong-bo

doi:10.3788/OPE.20142212.3272

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Optimization design of composite wing skin with honeycomb sandwich by genetic algorithm

更新时间：2020-08-13

- Optimization design of composite wing skin with honeycomb sandwich by genetic algorithm
- Optics and Precision Engineering Vol. 22, Issue 12, Pages: 3272-3279(2014)
- 作者机构：
  
  1. 中国科学院长春光学精密机械与物理研究所,吉林长春,中国,130033
  2. 中国科学院大学北京,中国,100049
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20142212.3272
  CLC： V224;V257
- Received：15 November 2013，
  
  Revised：27 January 2014，
  
  Published：25 December 2014
- 稿件说明：
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丁玲, 孙辉, 贾宏光等. 应用遗传算法优化设计机翼复合材料蜂窝夹层结构蒙皮[J]. 光学精密工程, 2014,22(12): 3272-3279

DING Ling, SUN Hui, JIA Hong-guang etc. Optimization design of composite wing skin with honeycomb sandwich by genetic algorithm[J]. Editorial Office of Optics and Precision Engineering, 2014,22(12): 3272-3279
丁玲, 孙辉, 贾宏光等. 应用遗传算法优化设计机翼复合材料蜂窝夹层结构蒙皮[J]. 光学精密工程, 2014,22(12): 3272-3279 DOI： 10.3788/OPE.20142212.3272.

DING Ling, SUN Hui, JIA Hong-guang etc. Optimization design of composite wing skin with honeycomb sandwich by genetic algorithm[J]. Editorial Office of Optics and Precision Engineering, 2014,22(12): 3272-3279 DOI： 10.3788/OPE.20142212.3272.

摘要

为提高无人机复合材料机翼蒙皮的强度

应用遗传算法优化设计了蜂窝夹层结构蒙皮的铺层.针对复合材料结构优化变量离散化的特点

设计了应用整数编码策略的遗传算法

并根据Tsai-Wu准则提出了适应度函数

参考复合材料的铺层原则给出了约束条件.然后

通过优化设计得到了最佳的蒙皮复合材料结构铺层方案.最后

通过有限元分析及静力试验验证了复合材料蜂窝夹层结构蒙皮设计的合理性.试验结果表明:左、右机翼翼梢的最大变形分别为116.02 mm和105.36 mm

小于性能要求的180 mm.探伤测试显示机翼复合材料结构没有出现损坏

满足机翼结构的工程指标要求.此机翼结构的无人机已成功完成了首飞试验

验证了设计结果的可信及工程可用性.

Abstract

To improve the strength of composite wing skin of a Unmanned Aerial Vehicle(UAV)

the stacking sequence of honeycomb sandwich structure wing skin was designed optimally by a genetic algorithm. According to the design variables' discrete characteristics of the composite

the genetic algorithm based on an integral code strategy was presented. In consideration of the Tsai-Wu criterion

the fitness function was proposed and the constrain conditions were given by the stacking sequence principle of composite laminate layout. Then

the optimized stacking sequence scheme for skin composite structure was obtained by optimization design. Finally

the rationality of the composite laminate layout was verified by finite element analysis and static experiments. The experimental results show that the maximum deformations of the left and right wing tips are 116.02 mm and 105.36 mm

respectively

which meet the requirements that the best deformation is less than 180 mm. Ultrasonic inspection was performed and no damage is detected

which means that the wing structure meets the demands of engineering applications. An UAV with the composite wing skin was flown out successfully

and it verifies the feasibility of proposed design.

关键词

Keywords

references

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