基于姿态反馈实现过载跟踪的飞行器控制方法

针对依靠气动力提供控制力和控制力矩的飞行器，在构建俯仰-偏航通道非线性数学模型的基础上，提出一种兼顾机动能力和姿态稳定性能的飞行器控制系统设计方法。基于飞行器过载与姿态的等效转换，将制导律计算的过载指令转化为姿态角指令，进而通过以姿态角反馈为主、过载补偿为辅的控制系统设计实现对过载指令的精确跟踪。通过频域相对稳定性分析，验证该方法的稳定性；通过飞行器6自由度仿真，验证该方法在各项随机误差下既能够实现制导对过载的跟踪要求，又达到对飞行器姿态进行鲁棒稳定控制的目的。研究结果表明，该方法简单可靠，具有良好的动态特性和很强的鲁棒性，已得到工程应用验证。

Aircraft Control Method Based on Attitude Feedback for Overload Tracking

For aircraft whose control forces and moments are provided by aerodynamic rudder, a method of the control system considering the maneuverability and attitude stability is proposed depending on the nonlinear mathematical model of the pitch and yaw channel. First, based on the equivalent conversion between the overload and attitude of aircraft, the accurate attitude angle command is obtained according to the overload command calculated by the guidance law. And then, using attitude feedback as the main control loop and overload compensation as the auxiliary, this control strategy enables the overload command to be tracked accurately. The six-degree-of-freedom simulation results demonstrate that the proposed method not only meets the requirements of overload tracking accuracy for guidance, but also achieves the purpose of robust stability control for aircraft attitude. This method is simple and reliable, and has been verified by engineering application.