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.

在高攻角的非线性飞行模式下运行的现代飞机的侧倾角运动通常表现出极限环振荡，这通常被称为机翼岩石现象。机翼岩石动力学由基本非线性的模型表示，其参数在很大范围内变化，这取决于飞行条件（高度，马赫数，有效载荷质量等）和迎角。机翼压制的一种透视方法在于适应方法。本文在隐式参考模型中应用简单自适应控制方法（IRM）被提出并进行了数值研究。应用IRM自适应控制器可确保平滑跟踪参考（期望）轨迹的侧倾角，同时防止机翼晃动。与以前的作者的工作相比，本文采用了更为复杂和现实的模型，其中在控制器设计阶段明确考虑了飞机侧倾和侧滑运动之间的相互依赖性以及副翼偏转角的限制。为此，提出了对IRM控制方案的修改并进行了数值研究。仿真结果表明该方法具有较高的效率。