Nonlinear fluid-structure interaction response analysis of a large flexible wing under strong gusts
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摘要:
大柔性机翼在较大阵风来流下会产生显著变形，其中，几何非线性和气动非线性不可忽略。为研究大柔性机翼在强阵风下的响应，建立了基于几何非线性梁理论与计算流体力学(CFD)方法的流固耦合分析方法。通过对比倒置柔性板风洞试验，验证了该流固耦合仿真的准确性。在此基础上，建立了半展弦比为9的大柔性机翼流体模型和几何非线性梁模型，在雷诺数为105的条件下，对其进行阵风响应计算，研究了不同阵风比下(
R G=0.1～0.4)大柔性机翼的动响应特性，特别是对大阵风比(R G=0.4)时阵风诱导的机翼动态失速气动特性进行分析。研究结果表明：随着阵风比的增大，机翼出现了显著的非线性弯曲变形，在R G=0.4时，机翼的最大弯曲变形达63%半展长，同时，机翼的弯曲变形使前缘涡(LEV)的展向分布宽度减小，影响了气动力的分布，降低了阵风载荷。Abstract:The geometric nonlinearity and aerodynamic nonlinearity cannot be ignored as the large flexible wing undergoes significant deformation when subjected to high gusts. In order to study the response of a large flexible wing under strong gusts, a fluid-structure interaction analysis method based on geometric nonlinear beam theory and computational fluid dynamics (CFD) was established. The fluid model and geometrically nonlinear beam model of a big flexible wing with a semi-aspect ratio of 9 were constructed, and the accuracy of the fluid-structure interaction simulation approach was confirmed by comparing wind tunnel tests of inverted flexible plate. The dynamic response characteristics of large flexible airfoils were examined at various gust ratios (
R G=0.1-0.4). In particular, the dynamic stall aerodynamic characteristics of the airfoils caused by gusts at large gust ratios (R G=0.4) were examined. The gust response analysis was conducted at a Reynolds number of 105. The results show that significant nonlinear bending deformation of the wing occurs with the increase of gust ratios, and the maximum bending deformation of the wing reaches 63% of the half-spread length atR G=0.4. Meanwhile, the bending deformation of the wing reduces the width of the spreading distribution of the leading-edge vortex (LEV), which affects the distribution of aerodynamic forces and reduces the gust loads.-
Key words:
- large flexible wing /
- nonlinear /
- fluid-structure interaction /
- gust response /
- dynamic stall
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图 5 U=4.2 m/s时仿真与实验位移对比
Figure 5. Comparison of simulation and experimental displacements at U=4.2 m/s
图 7 不同来流速度下倒置柔性板自由端位移曲线
Figure 7. Displacement curves of free end of an inverted flexible plate under different incoming flow velocities
图 8 仿真所得不同流速下倒置柔性板动态轮廓叠加
Figure 8. Dynamic contour superposition of an inverted flexible plate under different flow velocities obtained from simulation
图 18 工况2下不同时刻压力云图及变形
Figure 18. Pressure contours and deformation at different moments under case 2
图 19 工况1、2截面升力时空分布
Figure 19. Spatiotemporal distributions of the sectional lift for case 1 and case 2
图 20 C时刻机翼升力沿展向变化趋势及上表面压力分布
Figure 20. Trend of wing lift along the spreading direction and pressure distribution on the upper surface at the moment C
图 21 不同时刻机翼周围的Q准则等值面（Q = 2 000）
Figure 21. The Q-criterion iso-surfaces around the wing at different time (Q = 2 000)
图 24 工况4下不同时刻压力云图及变形
Figure 24. Pressure contours and deformation at different moments under case 4
图 25 工况3、4截面升力时空分布
Figure 25. Spatiotemporal distributions of the sectional lift for case 3 and case 4
图 26 不同时刻机翼周围的 Q 准则等值面（Q = 5 000）
Figure 26. The Q-criterion iso-surfaces around the wing at different time (Q = 5 000)
图 27 c时刻机翼升力沿展向变化趋势及上表面压力分布
Figure 27. Trend of wing lift along the spreading direction and pressure distribution on the upper surface at the moment c
表 1 时间和空间离散方案
Table 1. Time and space discrete schemes
设置项目 方案 瞬态 一阶隐式 梯度 基于单元的最小二乘法 压力 二阶 动量 二阶迎风 湍动能 二阶迎风 比耗散率 二阶迎风 
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表 2 倒置柔性板参数
Table 2. Parameters of inverted flexible plate
弹性模量/GPa 泊松比 密度/（kg·m−3） 板长/m 板宽/m 板厚/m 2.38 0.38 1200 0.27 0.3 0.0008
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表 3 机翼材料属性
Table 3. Material properties of the wing
结构 密度/(kg·m−3) 弹性模量/GPa 泊松比 柔性体翼梁 5 800 193.1 0.38 刚体翼肋 7 125 刚体翼尖配重 6 525
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表 4 前四阶模态频率
Table 4. Frequency of the first four modes
模态阶数 模态描述 模态频率/Hz 一 机翼面外一弯 2.46 二 机翼面外二弯 19.54 三 机翼面内一弯 23.87 四 机翼一扭 38.21
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表 5 网格参数
Table 5. Parameters of the mesh
网格名称 背景网格
数量前景网格
数量壁面距离 网格增长率 粗网格 862 580 294 524 1.5 1.23 中等网格 862 580 355 460 1.0 1.20 细网格 862 580 457 020 0.5 1.17
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表 6 仿真工况参数
Table 6. Simulated operating conditions parameters
工况编号 机翼刚柔性 机翼迎角/(°) 阵风速度幅值/
(m·s−1)RG 阵风频率/Hz 1 刚性 0 2.5 0.1 3 2 柔性 0 2.5 0.1 3 3 刚性 0 10 0.4 3 4 柔性 0 10 0.4 3
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