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

被引：0

作者：

Ding, Ling ^{[1
,2
]}

Sun, Hui ^{[1
]}

Jia, Hong-Guang ^{[1
]}

Yang, Hong-Bo ^{[1
]}

机构：

[1] Changchun Institute of Optics, Fine Mechanics and Physics, Chinese Academy of Sciences, Changchun

[2] University of Chinese Academy of Sciences, Beijing

来源：

Guangxue Jingmi Gongcheng/Optics and Precision Engineering | 2014年 / 22卷 / 12期

关键词：

Composite material; Genetic algorithm; Honeycomb sandwich; Stacking sequence optimization; Tsai-Wu criterion; Wing skin;

D O I：

10.3788/OPE.20142212.3272

中图分类号：

学科分类号：

摘要：

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. ©, 2014, Chinese Academy of Sciences. All right reserved.

引用

页码：3272 / 3279

页数：7

共 18 条

[1]

An Y., Jia X.Z., Zhang L., Et al., Optimization design of CFRP based main backbone with high stiffness ratio for space camera, Opt. Precision Eng., 21, 2, pp. 416-422, (2013)

[2]

He N., Yang J.B., Gao F., Application tendency of advanced composite materials for military unmanned aerial vehicles, Fiber Reinforced Plastics/Composites, 2, pp. 94-97, (2013)

[3]

Cheng W.L., Qiu Q.Y., Zhao B., Application progress of composites for UAV, Aeronautical Manufacturing Technology, 18, pp. 88-91, (2012)

[4]

Li W., Liu H.W., Structure stability of precision component made of carbon fiber composite in space optical remote sensor, Opt. Precision Eng., 16, 11, pp. 2173-2179, (2008)

[5]

Xiu Y.S., Cui D.G., Optimization design of composite sandwich structure, Journal of Beijing University of Aeronautics and Astronautics, 30, 9, pp. 855-858, (2004)

[6]

Chang N., Zhao M.Y., Wang W., Et al., Efficiently optimization skin of composite wing structure with PATRAN/NASTRAN, Journal of Northwestern Poly Technical University, 24, 3, pp. 326-329, (2006)

[7]

Feng X.B., Huang H., Wang W., Strength optimization of large wind turbine blade root on the genetic algorithm, Acta Material Composite Sinica, 29, 5, pp. 196-202, (2012)

[8]

Liang H.Z., Zhang Y.L., Optimization design of composite wing beam with honeycomb sandwich, Machine Building Automation, 38, 3, pp. 3-5, (2009)

[9]

Hirano Y., Todoroki A., Fractal branch and bound method for staking-sequence optimization of composite delta wing, (2004)

[10]

Abouhamze M., Shakeri M., Multi-objective stacking sequence optimization of laminated cylindrical panels using a genetic and neural networks, Composite Structure, 81, 2, pp. 253-263, (2007)

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