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首页> 外文期刊>Journal of Computer and Systems Sciences International >On Unsteady Aerodynamic Airfoil Loads in the Design of a Control System for Minimizing the Effect of Wind Perturbations Using the Rudder on the Trailing Edge of the Wing
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On Unsteady Aerodynamic Airfoil Loads in the Design of a Control System for Minimizing the Effect of Wind Perturbations Using the Rudder on the Trailing Edge of the Wing

机译：关于控制系统设计中的非稳态气动翼型载荷，该控制系统使用机翼后缘上的舵将风摄动的影响最小化

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摘要

The problem of minimizing wind perturbations using the control on the trailing edge of the airfoil is considered for an airfoil passing through a short wind gust. It is considered that the airfoil movement is bounded by two degrees of freedom, viz. in pitch and height, and each channel has an elastic spring that simulates torsional and bending stiffness of the wing. The study is held on the basis of the developed mathematical model for unsteady aerodynamic loads (the lift coefficient and the pitching moment) when a thin two-dimensional airfoil is flowed without separation by a flow of ideal incompressible fluid. The results obtained using this mathematical model and the conventional quasi-steady model on the basis of aerodynamic derivatives are compared. It is shown that the stability properties for the quasi-steady and unsteady aerodynamics models differ in a wide range of parameters of the airfoil movement considered. Moreover, taking into account the unsteadiness of aerodynamics when designing a control system allows us to suppress the wind perturbations more efficiently and counts when determining the requirements on the actuator rates necessary to suppress wind gusts of high amplitude.
机译：对于通过短阵风的翼型，考虑了使用翼型后缘上的控件将风扰最小化的问题。认为机翼运动受到两个自由度的限制。在俯仰和高度方面，每个通道都有一个弹性弹簧，可以模拟机翼的扭转和弯曲刚度。该研究是基于已开发的数学模型进行的，当数学模型薄薄的二维翼型在没有理想的不可压缩流体流动而没有分离的情况下流动时，产生了不稳定的空气动力学载荷（升力系数和俯仰力矩）。比较了使用该数学模型和基于空气动力学导数的常规准稳态模型获得的结果。结果表明，拟稳态和非稳态空气动力学模型的稳定性在所考虑的翼型运动参数范围内都不同。此外，在设计控制系统时考虑到空气动力学的不稳定性，我们可以更有效地抑制风的扰动，并在确定对抑制高振幅的阵风所需的执行器速率的要求时进行计数。

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