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基于变弯度后缘的机翼阵风响应减缓数值研究

尉濡恺 戴玉婷 杨超 于思恒

尉濡恺,戴玉婷,杨超,等. 基于变弯度后缘的机翼阵风响应减缓数值研究[J]. 北京航空航天大学学报,2023,49(7):1864-1874 doi: 10.13700/j.bh.1001-5965.2021.0563
引用本文: 尉濡恺,戴玉婷,杨超,等. 基于变弯度后缘的机翼阵风响应减缓数值研究[J]. 北京航空航天大学学报,2023,49(7):1864-1874 doi: 10.13700/j.bh.1001-5965.2021.0563
WEI R K,DAI Y T,YANG C,et al. Numerical study of wing gust response alleviation based on camber morphing trailing edge[J]. Journal of Beijing University of Aeronautics and Astronautics,2023,49(7):1864-1874 (in Chinese) doi: 10.13700/j.bh.1001-5965.2021.0563
Citation: WEI R K,DAI Y T,YANG C,et al. Numerical study of wing gust response alleviation based on camber morphing trailing edge[J]. Journal of Beijing University of Aeronautics and Astronautics,2023,49(7):1864-1874 (in Chinese) doi: 10.13700/j.bh.1001-5965.2021.0563

基于变弯度后缘的机翼阵风响应减缓数值研究

doi: 10.13700/j.bh.1001-5965.2021.0563
基金项目: 国家自然科学基金(11672018)
详细信息
    作者简介:

    尉濡恺 男,硕士。主要研究方向:变体飞行器设计

    戴玉婷 女,博士,副教授,博士生导师。主要研究方向:气动弹性力学

    杨超 男,博士,教授,博士生导师。主要研究方向:气动弹性力学

    通讯作者:

    E-mail:yutingdai@buaa.edu.cn

  • 中图分类号: V211.47;TB553

Numerical study of wing gust response alleviation based on camber morphing trailing edge

Funds: National Natural Science Foundation of China (11672018)
More Information
  • 摘要:

    针对带有变弯度后缘的机翼建立了阵风响应分析的数学模型,并开展了阵风响应减缓的仿真研究。采用计算流体力学(CFD)方法计算变弯度后缘给定动态偏转运动下的广义非定常气动力,并基于状态观测器法辨识CFD数据建立后缘动态偏转下的广义气动力模型,采用面元法计算模态运动、阵风引起的广义气动力,利用广义预测控制(GPC)方法设计阵风减缓控制律,在此基础上对变弯度后缘与传统铰链舵面动态气动力特性进行对比。仿真结果表明:基于变弯度后缘的GPC方法能够有效减缓由阵风引起的机翼翼尖加速度响应,翼尖加速度减缓效率为44.33%;相比传统铰链舵面,变弯度后缘偏转时弦向剖面上下表面压力分布更连续,相同舵偏下对机翼动态气动力影响更大,阵风响应减缓效率也更高,采用变弯度后缘进行阵风减缓具有更为广阔的应用前景。

     

  • 图 1  变弯度机翼几何模型

    Figure 1.  Camber morphing wing geometry model

    图 2  前4阶模态振型

    Figure 2.  The first four modes shape

    图 3  流域尺寸及翼面网格示意图

    Figure 3.  Schematic diagram of watershed size and airfoil mesh

    图 4  流场特性分析

    Figure 4.  Flow field characteristic analysis

    图 5  变弯度后缘偏转广义模态气动力辨识结果

    Figure 5.  Identification result of generalized modal aerodynamic force of trailing edge deflection

    图 6  不同后缘运动幅值气动力预测

    Figure 6.  Aerodynamic prediction of different trailing edge motion amplitudes

    图 7  闭环阵风响应减缓仿真结果

    Figure 7.  Simulation results of closed-loop gust response alleviation

    图 8  铰链舵面与变弯度后缘动态气动力对比

    Figure 8.  Comparison of aerodynamic forces between hinged flap and camber morphing trailing edge

    图 9  铰链舵面偏转广义模态气动力辨识结果

    Figure 9.  Identification result of generalized modal aerodynamic force of hinged flap deflection

    图 10  铰链舵面闭环阵风响应减缓仿真结果

    Figure 10.  Simulation results of closed-loop gust response alleviation based on hinged flap

    表  1  前4阶模态频率

    Table  1.   Frequency of the first four modes

    模态阶数模态描述模态频率/Hz
    1机翼面外一弯2.77
    2机翼面内一弯13.45
    3机翼面外二弯16.31
    4机翼一扭20.25
    下载: 导出CSV

    表  2  网格无关性计算

    Table  2.   Grid-independent computing

    网格名称网格数量升力系数
    Coarse420万0.091 8
    Medium538万0.083 2
    Fine631万0.083 4
    下载: 导出CSV
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  • 被引次数: 0
出版历程
  • 收稿日期:  2021-09-22
  • 录用日期:  2021-11-26
  • 网络出版日期:  2022-01-27
  • 整期出版日期:  2023-07-31

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