Modeling and analysis of slipstream effect during powered yaw control in distributed electric propulsion aircraft
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摘要:
在推力差动过程中，不同推进器滑流效应对覆盖区域的升力与阻力影响不同，会产生附加的横侧向力矩，这是动力偏航控制中必须考虑的因素。建立了涡管涡环耦合模型评估分布式电推进器与机翼之间的气动干扰。通过模型计算偏航过程中由螺旋桨滑流效应引起的横侧向力矩，完善了考虑滑流效应的分布式电推进飞机横航向飞行动力学方程，并构造了动力偏航控制器。进行动力偏航仿真，从偏航过程中截取一个时刻的飞行状态，将模型计算结果与CFD仿真结果进行对比。对比结果显示，涡管涡环耦合模型可有效刻画分布式电推进飞机偏航过程中滑流效应对机翼的气动影响，其中，由滑流效应产生滚转力矩的计算误差为3.22%，耗时小于5 min。
Abstract:During the process of differential thrust, the slipstream effect of the electric propulsors has varying impacts on lift and drag distribution, resulting in additional lateral moments. This is a critical consideration in yaw control. To address this issue, a vortex-tube vortex-ring coupling model was established to evaluate the aerodynamic interference between the electric propulsors and wing. Utilizing the established model, the effects of propeller slipstream on the lateral moment were computed. This refinement enabled consideration of the slipstream effect in the lateral-directional flight dynamics equations for distributed electric propulsion aircraft, and facilitated the design of a powered yaw control system. Yaw control simulations were conducted. The computed results were compared with the CFD results by capturing a moment in-flight during yaw. The simulation results demonstrated that the established vortex tube-vortex ring coupled model effectively captured the slipstream effect on the wing of the distributed electric propulsion system. Specifically, the calculation error for the roll moment generated by slipstream effects was 3.22%, and the computation time was less than 5 min.
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图 3 螺旋桨叶素受力分析与速度分解图
Figure 3. Blade element forces and velocity components of propeller
图 4 电推进器螺旋桨滑流涡丝微元段诱导速度
Figure 4. Induced velocity by vortex filament elements in the slipstream of propeller
图 10 动力偏航时非线性动态逆控制器输出的控制指令
Figure 10. Control commands given by NDI controller during powered yaw
图 11 动力偏航过程中不同位置螺旋桨推力对比
Figure 11. Comparison of propeller thrusts at different positions during powered yaw
表 1 算例中分布式电推进飞机参数
Table 1. Parameters used in case studies
部件 参数 数值或说明 机翼 展长b/m 9.639 总面积S/m2 6.194 翼根弦长croot/m 0.756 翼尖弦长ctip/m 0.529 平均气动弦长 cMAC/m 0.649 前缘后掠角 χ/（°） 1.887 展弦比 15.000 翼型 GAW-1 螺旋桨 直径 Dpropeller/m 0.576 轮毂直径 dhub/m 0.144 桨叶数目 5 额定转速 n/（r/min） 4548 最大转速 nmax/（r/min） 5500 桨叶角 β0.7/（°） 28.600 翼型 MH114 
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表 2 动力偏航算例本文模型与CFD计算结果对比
Table 2. Comparison of this paper’s method with CFD results during powered yaw used in case studies
参数 数值/（N·m） 误差/% 本文模型 CFD 由差动产生的偏航力矩 558.04 515.85 8.18 滑流效应引起滚转力矩 86.89 84.18 3.22 滑流效应引起偏航力矩 −11.45 −22.45
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