期刊文献+

具有执行器饱和的不确定系统的干扰抑制控制

Disturbance rejection control for uncertain systems with actuator saturation
下载PDF
导出
摘要 针对传统的干扰观测器(DO)设计并未考虑实际系统中普遍存在的执行器饱和问题,提出了一种具有抗饱和补偿的基于干扰观测器的控制(DOBC)策略.首先探究传统DOBC在执行器饱和时产生积分饱和现象的原因;然后通过最小化性能指标设计了一种抗积分饱和的补偿器,并将其与DO结合,使得修改后的DOBC能够有效处理执行器饱和;最后对所得闭环系统进行局部渐近稳定性分析.比较仿真结果表明,存在执行器饱和时,所提出控制方法具有更小的位置跟踪误差和干扰估计误差,并且设计的补偿器可以保持DO的状态尽可能接近没有执行器饱和时的状态,进而验证了所提出控制方法在抗干扰和抗饱和方面具有优越性. To address the issue that conventional disturbance observer(DO)design did not consider actuator saturation,which is prevalent in practical systems,a DO-based control(DOBC)strategy with anti-windup compensation is proposed.First,the reason of windup phenomenon in the conventional DOBC when the actuator is saturated is studied.Then,an anti-windup compensator is designed by minimizing the performance index,and patched to the DO so that the modified DOBC can effectively handle actuator saturation.Finally,local asymptotic stability analysis is performed on the resulting closed-loop systems.Comparative simulation results show that when there is actuator saturation,the proposed method has smaller errors in position tracking and disturbance estimation,and the designed compensator can maintain the DO states to be as close as possible to those without actuator saturation.This verifies that the proposed method is superior in anti-disturbance and anti-windup.
作者 苏金亚 谢鹏飞 李世华 Su Jinya;Xie Pengfei;Li Shihua(School of Automation,Southeast University,Nanjing 210096,China)
出处 《Journal of Southeast University(English Edition)》 EI CAS 2024年第2期120-128,共9页 东南大学学报(英文版)
基金 The National Natural Science Foundation of China(No.62303110) the Start-Up Research Fund of Southeast University(No.RF1028623226)。
关键词 抗积分饱和 干扰观测器 动态补偿器 执行器饱和 anti-windup disturbance observer dynamic compensator actuator saturation
  • 相关文献

参考文献3

二级参考文献16

  • 1管萍,陈家斌.挠性卫星的自适应模糊滑模控制[J].航天控制,2004,22(4):62-67. 被引量:8
  • 2Bilimoria K D, Wie B. Time-optimal three axis reori- entation of a rigid spacecraft [ J ]. Journal of Guid- ance, Control and Dynamics, 1993, 16( 3 ) : 446-452.
  • 3Hecht C. Homing guidance using angular acceleration of the line of sight [ C ]//Processing of the MAA Guidance, Navigation and Control Conference. New Orleans, LA, USA, 1991:856-869.
  • 4Robinettr P G. Spacecraft Euler parameter tracking of large-angle maneuvers via sliding mode control [ J ]. Journal of Guidance, Control and Dynamics, 1996, 19 (3) : 702 - 703.
  • 5Song C H, Kim S J, Kim S H, et al. Robust control of the missile attitude based on quatemion feedback [ J ]. Control Engineering Practice, 2006, 14(7) : 811 -818.
  • 6Banga H, Ha C K, Kim J H. Flexible spacecraft atti- tude maneuver by application of sliding mode control [ J]. Acta Astronautica, 2005, 57( 11 ) : 841 - 850.
  • 7Hu Q L, Ma G F. Variable structure control and active vibration suppression of flexible spacecraft during atti- tude maneuver [J ]. Aerospace Science and Technolo- gy, 2005, 9(4) : 307 -317.
  • 8Shtessel Y B, Shkolnikov A, Levant I A. Smooth sec- ond-order sliding modes: missile guidance application [ J ]. Automatica, 2007, 43 (8) : 1470 - 1476.
  • 9Levant I A. Higher-order sliding modes, differentiation and output-feedback control[J]. International Journal of Control, 2002, 76(9) : 924 -942.
  • 10程英容,张奕群.基于四元数反馈线性化的飞行器姿态控制方法研究[J].航天控制,2007,25(5):13-16. 被引量:9

共引文献11

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部