基于有限时间控制的高超声速飞行器控制律设计  

Control law design of hypersonic vehicle based on finite-time control

作　　者：王钊[1] 李世华[2] 费树岷[2] 

机构地区：[1]中国石油大学(华东)信息与控制工程学院,东营257061 [2]东南大学自动化学院,南京210096

出　　处：《东南大学学报（自然科学版）》2011年第5期1024-1029,共6页Journal of Southeast University：Natural Science Edition

基　　金：国家自然科学基金资助项目(61074013;91016004;60835001);新世纪优秀人才计划资助项目(NCET-10-0328);国家教育部博士点基金资助项目(20090092110022);山东省优秀中青年科学家科研奖励基金资助项目(BS2011DX040)

摘　　要：针对高超声速飞行器的飞行控制问题,提出了一种基于有限时间控制技术的控制方法.根据高超声速飞行器纵向模型的特点,将高度控制和速度控制看作2个子系统分别设计控制器.采用非线性动态逆与有限时间控制技术相结合的方法,分别设计了速度控制器和高度控制器.速度控制器设计时考虑了发动机的动态,使得飞行速度在有限时间内收敛到给定值.飞行高度控制中,首先针对航迹倾角设计有限时间控制器,使得航迹倾角在有限时间内收敛到给定值,然后根据航迹倾角和飞行高度一一对应的关系,使得飞行高度快速收敛到给定值.仿真结果表明,所提出的控制方法是有效的.A control method based on finite-time control technology is proposed for hypersonic vehicle flight control.According to the characteristics of the hypersonic vehicle longitudinal mode,velocity control and altitude control are considered as two subsystems to design controllers respectively.The design of velocity controller and altitude controller is conducted by combining nonlinear dynamic inverse control with finite-time control technique.The engine dynamics is considered during velocity controller design and the velocity can converge to a desired value in finite time under the proposed controller.In order to control flight attitude,first,a finite-time controller is designed for flight-path angle to make it converge to a desired value in finite time,and then according to the one to one correspondence between flight-path angle and altitude,the altitude rapidly converges to a desired value.The simulation results demonstrate that the method is valid.

关 键 词：高超声速飞行器 飞行控制 有限时间控制 动态逆 非线性 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置]