Numerical study of wing gust response alleviation based on camber morphing trailing edge
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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。
Abstract:A mathematical model for gust response analysis is established for a wing with camber morphing trailing edges, and a simulation study of gust response alleviation is carried out. The computational fluid dynamics method is used to calculate the generalized unsteady aerodynamic force under the given dynamic morphing of the trailing edge, and the generalized aerodynamic force model under the dynamic deflection of the trailing edge is established based on the state observer method,. The panel method is used to calculate the generalized aerodynamic force caused by mode motion and gust, while the generalized predictive control (GPC) method is used in the design of gust alleviation control law. On this basis, the aerodynamic characteristics of the camber morphing trailing edge and the traditional hinged flap are compared. The simulation results show that the GPC method based on the camber morphing trailing edge can effectively alleviate the wing-tip acceleration response caused by gust, and the wing-tip acceleration reduction efficiency is 44.25%. The wing with morphing trailing edge has a more continuous pressure distribution on the upper and lower surfaces, a greater impact on the aerodynamics, and higher acceleration reduction efficiency. The use of camber morphing trailing edges for gust alleviation has a broader application prospect.
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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 
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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 Coarse 420万 0.091 8 Medium 538万 0.083 2 Fine 631万 0.083 4
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