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不确定航空发动机分布式控制系统自适应滑模控制

任立通 谢寿生 王磊 苗卓广 彭靖波

任立通, 谢寿生, 王磊, 苗卓广, 彭靖波. 不确定航空发动机分布式控制系统自适应滑模控制[J]. 航空动力学报, 2017, 32(8): 2032-2040. doi: 10.13224/j.cnki.jasp.2017.08.029
引用本文: 任立通, 谢寿生, 王磊, 苗卓广, 彭靖波. 不确定航空发动机分布式控制系统自适应滑模控制[J]. 航空动力学报, 2017, 32(8): 2032-2040. doi: 10.13224/j.cnki.jasp.2017.08.029
Adaptive sliding mode control for uncertain aero-enginedistributed control system[J]. Journal of Aerospace Power, 2017, 32(8): 2032-2040. doi: 10.13224/j.cnki.jasp.2017.08.029
Citation: Adaptive sliding mode control for uncertain aero-enginedistributed control system[J]. Journal of Aerospace Power, 2017, 32(8): 2032-2040. doi: 10.13224/j.cnki.jasp.2017.08.029

不确定航空发动机分布式控制系统自适应滑模控制

doi: 10.13224/j.cnki.jasp.2017.08.029
基金项目: 国家自然科学基金(51476187, 51506221, 51606219); 陕西省自然科学基础研究计划(2015JQ5179,2015JM5207)

Adaptive sliding mode control for uncertain aero-enginedistributed control system

  • 摘要: 针对存在参数摄动、外部干扰的航空发动机不确定性分布式控制系统,在系统具有时变输入时延和干扰上界未知的情况下,设计了具有鲁棒性能的自适应滑模控制器。基于预测控制和矩阵奇异值理论,对初始的发动机离散分布式模型进行等效线性变换,得到不显含时延项的规范形系统模型,便于进行滑模面参数的求解;在给定的H∞指标下,推导了滑模运动在非匹配不确定性作用下渐进稳定的充分条件,给出了线性矩阵不等式(LMI)形式的滑模面参数设计方法;最后,设计对干扰具有估计功能的自适应率,在此基础上提出自适应滑模控制器。仿真结果表明:所设计的控制器能够有效降低外部干扰对系统动态性能的影响,在所考虑的不确定性因素作用下,系统的滑模运动具有理想的H∞性能。当外部干扰强度变化时,控制器的鲁棒性较好,状态收敛时间小于0.8s,且不存在抖振。

     

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出版历程
  • 收稿日期:  2015-11-20
  • 刊出日期:  2017-08-28

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