摘要
针对倾斜转弯高超声速飞行器滚动通道控制中初始误差大、系统参数不确定和干扰严重的问题,设计了一种自适应全局积分滑模控制方法。该方法在滑模控制参数中引入了自适应调节律来逼近系统参数摄动和干扰的上界,保证了整个控制过程中的滑模可达性,在此基础上,设计了一种基于全局积分滑模面的自适应滑模控制器,消除了稳态误差,同时大大削弱了系统参数不确定和干扰对系统的动态影响,并使系统在初始阶段就处于滑模态,解决了大的初始误差引起的超调问题。理论分析和仿真结果验证了本文所提方法的有效性。
Due to the large initial errors,uncertainties and disturbances in roll-channel of bank-to-turn hypersonic vehicle,an adaptive global integral sliding mode control approach is proposed.An adaptive parameter adjuster control rule was introduced into the sliding mode control,with the adaptive law adjusting parameter of the sliding mode controller to approximate the upper bound of parameter uncertainties and disturbances,which ensures the reachability of the sliding-mode during the whole control process.On the basis of this,an adaptive sliding mode control based on global integral sliding-mode is proposed.With this mode,the steady-state tracking error was eliminated while the system lies on the sliding-mode from beginning of any initial state.It also can avoid large overshoots due to the large initial errors and can effectively weaken the dynamic influence of parameters uncertainties and disturbances.Theoretical analysis and simulation results show the effectiveness of the proposed global integral sliding mode control scheme.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2012年第2期114-118,共5页
Journal of National University of Defense Technology
基金
国家自然科学基金资助项目(10302031)
关键词
倾斜转弯
高超声速
自适应控制
全局积分滑模
bank-to-turn
hypersonic
adaptive control
global integral sliding mode
