基于载荷设计的电动飞机复合材料机翼结构优化方法及试验验证
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V224+.3

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辽宁省自然科学基金(No. 20180550824)


Structural optimization and experimental verification of composite wing of electric aircraft based on aeroelastic load
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    摘要:

    基于柔度法静气弹分析方法,对电动飞机复合材料机翼考虑气动弹性载荷的结构优化方法进行研究。以考虑翼型弯度的涡格法计算机翼气动载荷,并与CFD计算结果进行对比,验证其准确性。使用遗传算法对机翼结构进行铺层优化,以铺层度及铺层角度百分比为优化变量,结构重量最低为优化目标,强度及复合材料工艺性作为设计约束,对机翼结构进行优化,计算强度时考虑气动弹性载荷。最后通过静力试验验证仿真结果的准确性。研究表明直机翼考虑气动弹性载荷后翼根弯矩、剪力及扭矩均有增加,基于该优化方法可设计合适的机翼结构刚度,在满足强度设计要求同时能达到减重目的。

    Abstract:

    Based on flexibility aeroelastic analysis method, the structural optimization method of electric aircraft composite wing considering aeroelastic load was studied in this paper. The aerodynamic load of the wing was calculated by the doublet lattice method considering the airfoil camber, and compared with the CFD results to verify its accuracy. With the ply orientation angle and percentage as the variables, the minimum structural weight as the objective, the strength and the composite material processability as constraints, the genetic algorithm was used to optimize the wing structure. In the strength calculation, the aeroelastic load correction caused by the deformation of the wing was considered. Finally, the accuracy of the simulation results was verified by a static experiment. The research shown that the wing root bending moment, shear force and torque of the straight wing have increased after considering the aeroelastic load, and an appropriate wing structure stiffness can be designed to meet the requirements of strength design and achieve weight reduction, based on this optimization method.

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李东辉,杨凤田,马宏图,等. 基于载荷设计的电动飞机复合材料机翼结构优化方法及试验验证[J]. 科学技术与工程, 2020, 20(18): 7516-7523.
Li Donghui, Yang Fengtian, Ma Hongtu, et al. Structural optimization and experimental verification of composite wing of electric aircraft based on aeroelastic load[J]. Science Technology and Engineering,2020,20(18):7516-7523.

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  • 收稿日期:2020-01-10
  • 最后修改日期:2020-05-06
  • 录用日期:2020-01-31
  • 在线发布日期: 2020-07-28
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