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面向扑翼翼面运动参数的优化设计

吴越 谢长川 杨超 安朝

吴越, 谢长川, 杨超, 等 . 面向扑翼翼面运动参数的优化设计[J]. 北京航空航天大学学报, 2022, 48(7): 1324-1331. doi: 10.13700/j.bh.1001-5965.2021.0593
引用本文: 吴越, 谢长川, 杨超, 等 . 面向扑翼翼面运动参数的优化设计[J]. 北京航空航天大学学报, 2022, 48(7): 1324-1331. doi: 10.13700/j.bh.1001-5965.2021.0593
WU Yue, XIE Changchuan, YANG Chao, et al. Optimal design of motion parameters of flapping wing[J]. Journal of Beijing University of Aeronautics and Astronautics, 2022, 48(7): 1324-1331. doi: 10.13700/j.bh.1001-5965.2021.0593(in Chinese)
Citation: WU Yue, XIE Changchuan, YANG Chao, et al. Optimal design of motion parameters of flapping wing[J]. Journal of Beijing University of Aeronautics and Astronautics, 2022, 48(7): 1324-1331. doi: 10.13700/j.bh.1001-5965.2021.0593(in Chinese)

面向扑翼翼面运动参数的优化设计

doi: 10.13700/j.bh.1001-5965.2021.0593
详细信息
    通讯作者:

    谢长川, E-mail: xiechangc@buaa.edu.cn

  • 中图分类号: V222;TB553

Optimal design of motion parameters of flapping wing

More Information
  • 摘要:

    扑翼机的飞行依赖于扑翼翼面的运动,经过优化的运动策略能够使特定翼面发挥最佳的气动性能。然而目前扑翼机设计中缺乏有效的运动参数优化方法,无法针对给定机翼确定一组最优运动参数。采用非定常涡格法(UVLM)计算扑翼气动力,与现有的实验数据进行对比,验证了气动力计算方法的准确性。基于DIRECT(矩形分割)全局优化算法,以最大化推进效率为特定优化目标,对扑翼运动参数进行了迭代优化。结果表明,通过该优化算法能够得到最优扑翼运动参数,有效提高特定气动性能;应用优化算法计算得到的平均推力与基准运动的平均推力相比,在数值上有1.04倍的提高。在设计过程中,降低气动力约束有利于扑翼运动优化,使给定扑翼翼面具有更大的推进效率,无气动力约束的最大推进效率与基准运动的推进效率相比提高了46.8%。

     

  • 图 1  二维Shubert函数

    Figure 1.  Plot of two-dimensional Shubert function

    图 2  最小值计算结果随迭代次数的变化

    Figure 2.  Minimum value vs. number of iterations

    图 3  DIRECT全局优化算法在搜索域中的采样情况

    Figure 3.  Sampling of DIRECT global optimization algorithm in search domain

    图 4  扑翼机翼上下简谐振荡的运动示意图

    Figure 4.  Schematic diagram of vertical-harmonic-oscillating flapping wing motion

    图 5  扑翼运动非定常涡格法动态网格的三维视图

    Figure 5.  Three-dimensional view of UVLM dynamic mesh caused by flapping motion

    图 6  完整扑翼周期内的升力系数变化

    Figure 6.  Lift coefficient caused by flapping motion in a complete cycle

    图 7  扑翼机翼绕点扑动和俯仰的耦合运动

    Figure 7.  Schematic diagram of coupled flapping wing motion of flapping and pitching around a point

    图 8  仿生扑翼运动学的俯仰角度和扑动角度

    Figure 8.  Pitch angle and translation distance of bionic flapping motion

    图 9  三种运动参数下扑翼运动的升力系数和推力系数

    Figure 9.  Lift coefficient and thrust coefficient under flapping motion with three sets of parameters

    图 10  单个周期的气动力分布

    Figure 10.  Time slice of aerodynamic distribution in a period

    图 11  最大推进效率随优化迭代次数的变化

    Figure 11.  Maximum propulsion efficiency vs. number of optimization iteration

    表  1  DIRECT全局优化算法的最优运动学结果

    Table  1.   Optimal kinematics results of DIRECT global optimization algorithm

    项目 基准运动参数 有气动力约束 无气动力约束
    θ0/(°) 5.46 5.28 -0.17
    γm/(°) 27.86 35.73 25.32
    η 0.222 0.235 0.326
    D/N -0.095 -0.194 -0.111
    L/N 0.414 0.414 -0.006
    下载: 导出CSV
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出版历程
  • 收稿日期:  2021-10-09
  • 录用日期:  2021-11-14
  • 刊出日期:  2021-11-22

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