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基于非定常气动力降阶的AGARD445.6硬机翼不同迎角颤振研究

容浩然 戴玉婷 许云涛 杨超

容浩然, 戴玉婷, 许云涛, 杨超. 基于非定常气动力降阶的AGARD445.6硬机翼不同迎角颤振研究[J]. 工程力学, 2022, 39(12): 232-247. doi: 10.6052/j.issn.1000-4750.2021.07.0559
引用本文: 容浩然, 戴玉婷, 许云涛, 杨超. 基于非定常气动力降阶的AGARD445.6硬机翼不同迎角颤振研究[J]. 工程力学, 2022, 39(12): 232-247. doi: 10.6052/j.issn.1000-4750.2021.07.0559
RONG Hao-ran, DAI Yu-ting, XU Yun-tao, YANG Chao. RESEARCH ON THE FLUTTER CHARACTERISTCIS OF AGARD445.6 SOLID WING CONSIDERING THE INITIAL ANGLE OF ATTACK BASED ON REDUCED ORDER MODEL[J]. Engineering Mechanics, 2022, 39(12): 232-247. doi: 10.6052/j.issn.1000-4750.2021.07.0559
Citation: RONG Hao-ran, DAI Yu-ting, XU Yun-tao, YANG Chao. RESEARCH ON THE FLUTTER CHARACTERISTCIS OF AGARD445.6 SOLID WING CONSIDERING THE INITIAL ANGLE OF ATTACK BASED ON REDUCED ORDER MODEL[J]. Engineering Mechanics, 2022, 39(12): 232-247. doi: 10.6052/j.issn.1000-4750.2021.07.0559

基于非定常气动力降阶的AGARD445.6硬机翼不同迎角颤振研究

doi: 10.6052/j.issn.1000-4750.2021.07.0559
基金项目: 国家自然科学基金项目(11672018)
详细信息
    作者简介:

    容浩然(1997−),男,湖北人,硕士生,主要从事气动弹性研究(E-mail: rhrsy@buaa.edu.cn )

    许云涛(1987−),男,河北人,博士生,主要从事气动弹性研究(E-mail: 18001033551@163.com)

    杨 超(1966−),男,安徽人,教授,博士,主要从事气动弹性研究(E-mail: yangchao@buaa.edu.cn)

    通讯作者:

    戴玉婷(1985−),女,湖北人,教授,博士,主要从事气动弹性研究(E-mail: yutingdai@buaa.edu.cn)

  • 中图分类号: V211.47

RESEARCH ON THE FLUTTER CHARACTERISTCIS OF AGARD445.6 SOLID WING CONSIDERING THE INITIAL ANGLE OF ATTACK BASED ON REDUCED ORDER MODEL

  • 摘要: 以AGARD445.6硬机翼为研究对象,发展了基于计算流体力学与模态叠加的并行流固耦合方法,计算该机翼在不同初始迎角、不同来流速度的气动弹性时域响应,结果表明:初始迎角小于7°时,该机翼颤振速度随着初始迎角增加而降低;初始迎角7°~10°,颤振速度随着迎角增大而增加。在10°迎角条件建立了基于径向基神经网络的非定常气动降阶模型,准确预测不同速度、减缩频率的非定常气动力,并使用时域龙格库塔法和频域VG法预测10°迎角的颤振特性;建立考虑初始迎角输入的非定常气动降阶模型,预测机翼不同初始迎角的颤振特性。基于降阶模型的初始迎角对颤振边界影响的机理分析表明:小迎角时,随着迎角的增加广义力系数幅值比增加,导致颤振速度的下降;迎角大于7°后展向涡改变了机翼表面压强分布,导致一扭广义力系数幅值比降低,从而增加该机翼颤振速度。
  • 图  1  径向基神经网络结构

    Figure  1.  Structure of RBFNN

    图  2  VFE-2计算网格

    Figure  2.  Mesh distribution of VFE-2

    图  3  不同截面压强系数分布CFD与试验对比

    Figure  3.  Pressure coefficient at various sections by CFD and experiment

    图  4  AGARD445.6计算网格

    Figure  4.  Mesh distribution of AGARD445.6 wing

    图  5  迎角10°90%展长处压强系数分布对比

    Figure  5.  The comparison result of pressure coefficient at 90% span and angle of 10°

    图  6  0°迎角不同来流条件广义位移响应

    Figure  6.  Time responses of wing tip displacement at various velocities (angle of 0°)

    图  7  计算状态点和颤振特性标准差误差棒

    Figure  7.  Calculation conditions and standard error bar of flutter boundary and frequency ratio

    图  8  10°迎角不同来流条件广义位移时域响应

    Figure  8.  Aeroelastic responses at different reduced velocities (angle of 10°)

    图  9  ROM1训练信号

    Figure  9.  Training signal of ROM1

    图  10  ROM2训练信号

    Figure  10.  Training signal of ROM2

    图  11  训练集、测试集包含的减缩频率、速度信息

    Figure  11.  Ranges of reduced frequencies and reduced velocities of training data set and test data set

    图  12  ROM1辨识结果

    Figure  12.  Identification results of ROM1

    图  13  ROM2辨识结果

    Figure  13.  Identification results of ROM2

    图  14  V*=0.428,不同减缩频率kAIC分量

    Figure  14.  AIC components at V*=0.428 and various reduced frequencies

    15  k=0.4,不同速度V*AIC分量

    15.  AIC components at k=0.4 and various reduced velocities

    图  16  基于ROM1,RK法的颤振预测

    Figure  16.  Flutter prediction by ROM1, RK method

    图  17  基于ROM2,RK法的颤振预测

    Figure  17.  Flutter prediction by ROM2 and RK method

    图  18  基于ROM1,VG法的颤振预测

    Figure  18.  Flutter prediction by ROM1 and VG method

    图  19  基于ROM2,VG法的颤振预测

    Figure  19.  Flutter prediction by ROM2 and VG method

    图  20  ROM3训练信号

    Figure  20.  Training signal of ROM3

    21  k=0.4,V*=0.443,不同迎角αAIC分量

    21.  AIC components at k=0.4, V*=0.443 and various angles of attack

    图  22  不同迎角ROM3颤振预测与流固耦合结果对比

    Figure  22.  Flutter prediction by ROM3 and CFD at various angles of attack

    图  23  k=0.4,V*=0.443,不同迎角α下的广义力系数fij与广义位移dj的幅值比和相位差

    Figure  23.  Amplitude ratio and phase between general force coefficient and general displacement at k=0.4, V*=0.443 and various angles of attack by ROM3

    24  机翼上表面压强云图和流线图

    24.  Pressure contour and streamline of the upper surface of the wing

    图  25  不同迎角展向90%截面的δCp弦向分布

    Figure  25.  δCp distribution at 90% span section for different angles

    图  26  90%展长截面广义力系数分布

    Figure  26.  Generalized force coefficients at 90% span section

    图  27  通过式(14)积分得到90%展长截面的广义力系数

    Figure  27.  Generalized force coefficients at 90% span section is obtained by integrating equation (14)

    表  1  迎角10°法向力系数Cn对比

    Table  1.   The comparison result of normal force coefficient Cn at angle of 10°

    网格量 最大y+ 法向力系数Cn 误差/(%)
    1.38×106 25 0.2320 0.3
    2.34×106 6 0.2313
    下载: 导出CSV

    表  2  AGARD445.6软机翼前两阶模态频率

    Table  2.   Mode frequency of AGARD445.6 weakened wing

    模态 一阶模态 二阶模态
    频率/Hz 9.60 38.17
    下载: 导出CSV

    表  3  试验与流固耦合计算结果对比

    Table  3.   Flutter results of CFD and experiment

    试验结果颤振速度/(m/s) 流固耦合颤振速度/(m/s) 误差/(%)
    172.46 171.4 0.61
    下载: 导出CSV

    表  4  AGARD445.6硬机翼前两阶模态频率

    Table  4.   Mode frequency of AGARD445.6 solid wing

    模态 一阶模态 二阶模态
    频率/Hz 14.12 50.91
    下载: 导出CSV

    表  5  ROM1和ROM2辨识误差

    Table  5.   Identification error of ROM1 and ROM2

    广义力系数 f11 f21 f12 f22
    ROM1 0.0160 0.0180 0.0352 0.0411
    ROM2 0.0332 0.0335 0.0435 0.0547
    下载: 导出CSV

    表  6  基于降阶模型的10°迎角颤振预测与流固耦合对比

    Table  6.   Flutter prediction by ROM and FSI, α = 10°

    颤振特性 颤振边界 $V_{\rm f}^*$ 频率比 $\omega {}_{\rm f}/{\omega _\alpha }$
    ROM1, RK法 0.487 0.74
    ROM1, VG法 0.489 0.72
    ROM2, RK法 0.472 0.77
    ROM2, VG法 0.477 0.74
    流固耦合 0.459-0.472 0.77~0.79
    下载: 导出CSV

    表  7  ROM3辨识误差

    Table  7.   Identification error of ROM3

    广义力系数 f11 f21 f12 f22
    ROM3A 0.0228 0.0210 0.0181 0.0095
    ROM3B 0.0283 0.0560 0.0222 0.0472
    下载: 导出CSV
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出版历程
  • 收稿日期:  2021-07-20
  • 录用日期:  2022-04-15
  • 修回日期:  2021-12-08
  • 网络出版日期:  2022-04-15
  • 刊出日期:  2022-12-01

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