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Aircraft wing rock oscillations suppression by simple adaptive control

机译：通过简单的自适应控制抑制飞机翼岩振荡

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摘要

Roll angular motion of the modern aircraft operating in non-linear flight modes with a high angle of attack often demonstrates the limit cycle oscillations, which is commonly known as the wing rock phenomenon. Wing rock dynamics are represented by a substantially non-linear model, with parameters varying over a wide range, depending on the flight conditions (altitude, Mach number, payload mass, etc.) and angle of attack. A perspective approach of the wing rock suppression lies in the adaptation methods. In the present paper an application of the simple adaptive control approach with the Implicit Reference Model (IRM) is proposed and numerically studied. The IRM adaptive controller is applied to ensure smooth tracking the roll angle of the reference (desired) trajectory with the simultaneous wing rock prevention. As compared with the previous authors' work, in the present paper more complex and realistic model is employed, where interdependence between aircraft roll and sideslip motions and the limitations on the aileron deflection angle are explicitly taken into account at the stage of the controller design. To this aim, the modification of the IRM control scheme is suggested and numerically studied. The simulation results obtained demonstrate high efficiency of the proposed method. (C) 2020 Elsevier Masson SAS. All rights reserved.
机译：在具有高攻角的非线性飞行模式下操作的现代飞机的角度运动通常会展示极限循环振荡，这是通常称为翼岩现象的限制循环振荡。翼岩动态由基本上非线性模型表示，参数随着宽范围而变化，取决于飞行条件（高度，马赫数，有效载荷质量等）和攻角。机翼岩石抑制的透视方法在于适应方法。在本文中，提出了具有隐式参考模型（IRM）的简单自适应控制方法的应用，并在数值上进行了研究。应用IRM自适应控制器，以确保与同时翼岩预防的参考（所需）轨迹的平滑跟踪滚动角度。与先前作者的工作相比，在本文中，采用更复杂和现实的模型，其中在控制器设计的阶段明确地考虑了飞机辊和侧滑运动与侧滑角的相互依存和侧射角的局限性。为此目的，建议和数值研究了IRM控制方案的修改。获得的仿真结果表明了该方法的高效率。 （c）2020 Elsevier Masson SAS。版权所有。

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