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考虑壁板刚度匹配的大型飞机复合材料机翼气动弹性优化设计

肖志鹏 钱文敏 周磊

肖志鹏, 钱文敏, 周磊等 . 考虑壁板刚度匹配的大型飞机复合材料机翼气动弹性优化设计[J]. 北京航空航天大学学报, 2018, 44(8): 1629-1635. doi: 10.13700/j.bh.1001-5965.2017.0613
引用本文: 肖志鹏, 钱文敏, 周磊等 . 考虑壁板刚度匹配的大型飞机复合材料机翼气动弹性优化设计[J]. 北京航空航天大学学报, 2018, 44(8): 1629-1635. doi: 10.13700/j.bh.1001-5965.2017.0613
XIAO Zhipeng, QIAN Wenmin, ZHOU Leiet al. Aeroelastic optimization design of composite wing for large aircraft with panel stiffness matching[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(8): 1629-1635. doi: 10.13700/j.bh.1001-5965.2017.0613(in Chinese)
Citation: XIAO Zhipeng, QIAN Wenmin, ZHOU Leiet al. Aeroelastic optimization design of composite wing for large aircraft with panel stiffness matching[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(8): 1629-1635. doi: 10.13700/j.bh.1001-5965.2017.0613(in Chinese)

考虑壁板刚度匹配的大型飞机复合材料机翼气动弹性优化设计

doi: 10.13700/j.bh.1001-5965.2017.0613
详细信息
    作者简介:

    肖志鹏  男, 博士, 高级工程师。主要研究方向:飞行器结构优化设计、复合材料结构设计

    钱文敏  男, 博士, 工程师。主要研究方向:飞机气动弹性设计、分析与试验

    周磊  男, 硕士, 工程师。主要研究方向:复合材料机翼结构设计与优化

    通讯作者:

    肖志鹏, E-mail: xiaozhipeng@comac.cc

  • 中图分类号: TB330.1;V211.47

Aeroelastic optimization design of composite wing for large aircraft with panel stiffness matching

More Information
  • 摘要:

    针对大型飞机复合材料机翼,发展了一种考虑壁板刚度匹配的气动弹性优化设计方法。基于敏度算法,以结构质量最小化为目标,以壁板刚度匹配、颤振速度、翼尖变形、设计许用值、工艺性等为约束,在严重载荷状态下设计复合材料机翼结构,研究不同壁板刚度匹配要求对于优化设计结果的影响,并与传统优化设计结果进行比较。结果表明:考虑壁板刚度匹配需要付出一定的结构质量,但对局部稳定性设计、损伤容限设计和大型复合材料壁板制造有利;壁板刚度匹配设计范围对于优化设计结果影响显著,需要根据设计和制造要求合理确定;压缩设计许用值是影响复合材料机翼气动弹性优化设计的关键约束。

     

  • 图 1  复合材料左机翼结构有限元模型

    Figure 1.  Structural finite element model of left composite wing

    图 2  复合材料左机翼气动力模型

    Figure 2.  Aerodynamic model of left composite wing

    图 3  复合材料机翼在严重载荷下的变形

    Figure 3.  Deformations of composite wings under critical load conditions

    图 4  复合材料机翼上蒙皮压缩应变(Case1)

    Figure 4.  Compression strain of up skin for composite wing (Case1)

    图 5  复合材料机翼结构相对质量

    Figure 5.  Relative mass of composite wing

    图 6  复合材料机翼下蒙皮屈曲稳定性分布

    Figure 6.  Buckling stability distribution of lower skin for composite wing

    表  1  复合材料机翼优化结果在严重载荷下的变形

    Table  1.   Deformations of optimal results for composite wings under critical load conditions

    刚度比约束 翼尖相对变形/% 翼尖扭角/(°)
    Case1 Case2 Case1 Case2
    不考虑刚度比 9.07 -3.08 1.42 0.98
    km∈[0.25, 0.5] 8.28 -2.82 1.33 0.90
    km∈[0.5, 0.75] 8.66 -2.94 1.19 0.89
    km∈[0.75, 1.0] 8.80 -2.98 1.25 0.92
    下载: 导出CSV

    表  2  复合材料机翼颤振速度

    Table  2.   Flutter speed of composite wings

    刚度比约束 颤振速度/(m·s-1)
    不考虑刚度比 407.8
    km∈[0.25, 0.5] 423.1
    km∈[0.5, 0.75] 407.4
    km∈[0.75, 1.0] 406.9
    下载: 导出CSV
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出版历程
  • 收稿日期:  2017-10-09
  • 录用日期:  2017-12-15
  • 刊出日期:  2018-08-20

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