基于LQR的纵向多自由度变稳控制律设计  

Design of control law for longitudinal multi-degrees of freedom variable stability based on LQR

作　　者：丁团结 

机构地区：[1]中航工业飞行仿真航空科技重点实验室,陕西西安710089

出　　处：《飞行力学》2016年第3期86-89,共4页Flight Dynamics

摘　　要：飞机进场着陆过程中,速度、迎角和俯仰角速度等多参数的跟踪模拟是一个复杂的多输入输出系统,采用传统的控制方法难以获得满意的控制效果。根据系统控制要求,提出一种利用最优二次型调节器(LQR)的控制方式。首先分析跟踪模拟的结构形式,把模型跟踪问题化为最优二次型状态调节器,确定控制律的基本结构;然后对某型飞机进场着陆阶段特性利用TIFS飞机进行模型跟踪控制律的设计,并结合经典控制理论对系统控制参数进行修正;最后利用舵机在回路的半物理试验台进行仿真。结果表明,所提出的LQR控制方法能够有效地解决多控制回路性能的自动协调,具有良好的动态响应,而且有很高的模型跟踪模拟精度。The tracing simulation of velocity,angle of attack and pitch angle rate is a complex,multi-input and multi output control system during approach and landing stage,while it is difficult to obtain the satisfactory feedback with the traditional control method. According to the requirements for system control,the control mode based on Linear Quadratic Regulator（ LQR） was proposed in this paper. Firstly,the structural form of tracing simulation was analyzed and the problem of model-following was transferred to linear quadratic regulating,so the basic structure of control law was determined. Then combining one actual flight test airplane,the Total In-Flight Simulator（ TIFS） was applied to design the control law for approach and landing stage,and the control parameter was modified based on classic control theory. Finally,the simulation was studied by steering engine in semi-physical test-bed environment with loop,and the results have shown that the control method in this paper can solve the automatic coordination of multiloop control performance efficiently with good dynamic feedback and high accuracy for simulation.

关 键 词：变稳飞机 模型跟踪 最优控制 多自由度 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]