基于简单自适应控制的滑模飞行重构控制律  

The reconfigurable flight control design of adaptive sliding mode control based on simple adaptive control

作　　者：齐晓慧[1,2] 杨志军[2] 吴晓蓓[1] 

机构地区：[1]南京理工大学自动化系,江苏南京210094 [2]军械工程学院光学与电子工程系,河北石家庄050003

出　　处：《飞行力学》2010年第4期37-41,共5页Flight Dynamics

基　　金："十一五"国防预研基金资助(51325050203)

摘　　要：为提高飞行重构控制系统的鲁棒性,提出了一种基于简单自适应控制的滑模变结构重构控制律设计方法。采用简单自适应控制取代传统的等效控制律,可以较好地解决原等效控制律求取完全取决于被控系统结构和参数以及计算复杂等问题;同时引入饱和函数替代符号函数来减弱变结构控制的抖振现象;利用李雅普诺夫稳定性理论分析了该重构飞行控制系统的稳定性;以某型飞机侧向飞行控制系统为例,进行了仿真分析与研究。结果表明,该方法对操纵面损伤等故障具有较强的适应能力,使重构飞行控制系统在跟踪参考输入信号时具有较好的鲁棒性。A design method of reconfigurable flight control law which is the adaptive sliding mode control based on a simple adaptive control,is presented in this paper for improving the robust stability of the reconfigurable flight control system.The equivalent control of SMC requires thorough knowledge of the controlled plant parameters and dynamics that is difficult to be obtained or may be unknown,and it is replaced with simple adaptive control to solve this problem.A saturation function is introduced in design of the sliding mode surface for weakening the chattering in SMC.The stability of the control system is analyzed by Lyaponov＇s theory.The simulation analyses are done for the configurable flight control system of an aircraft lateral model.The result shows that the effectiveness and feasibility of the proposed control law in cases of the aircraft control surface loss-of-effectiveness failures and the reconfigurable flight control system has better following track for reference signal.

关 键 词：自适应控制 滑模控制 简单自适应 重构控制律 

分 类 号：TP273.2[自动化与计算机技术—检测技术与自动化装置]