基于动态逆-PID的高超声速飞行器巡航姿态控制  

Dynamic inversion-PID based cruising attitude control of hypersonic vehicle

作　　者：吴雨珊 江驹[1] 甄子洋[1] 顾臣风 

机构地区：[1]南京航空航天大学自动化学院,江苏南京210016

出　　处：《飞行力学》2015年第2期145-149,共5页Flight Dynamics

基　　金：国家自然科学基金资助(61304223);教育部高等学校博士科学点专项科研基金(20123218120015);南京航空航天大学研究生创新基地(实验室)开发基金资助(kfjj201420);中央高校基本科研业务费专项资金资助

摘　　要：以某型高超声速飞行器为研究对象,针对巡航状态下气动参数不确定的姿态控制问题,提出了一种结合非线性动态逆控制与PID控制的姿态控制方法。首先,对高超声速飞行器非线性模型进行精确反馈线性化,得到了飞行器纵向姿态仿射非线性方程;接着,为速率变化快慢不同的迎角和俯仰角速率分别设计了动态逆控制律以抵消对象的非线性特性;然后,在动态逆控制的基础上,采用工程上易于实现的PID控制补偿由于未精确建模带来的系统逆误差,实现了迎角对指令信号的有效跟踪;最后,进行了数值仿真验证。结果表明,所设计的高超声速飞行器动态逆-PID姿态控制器具有良好的跟踪性能和鲁棒性能。This paper takes a nonlinear longitudinal model of a hypersonic vehicle as the object. One nonlinear dynamic inversion control method combined with PID control was put forward to deal with the uncertainty of hypersonic aerodynamic parameters. Firstly,the precise linearization equation was obtained from the nonlinear flight model. Next,the fast and slow subsystems were separated. The dynamic inversion control law was designed for each subsystem to offset the nonlinear part. Then,the engineering easyrealized PID control theory was used to compensate the system inversion error. Finally,the dynamic inversion-PID controller is shown to have good dynamic responses and robustness.

关 键 词：高超声速飞行器 姿态控制 非线性动态逆控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]