| 不确定航空发动机分布式控制系统自适应滑模控制 |
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| 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. |
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| 作者姓名： | 任立通 谢寿生 王磊 苗卓广 彭靖波 |
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| 作者单位： | 1.空军工程大学 航空航天工程学院，西安 710038 |
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| 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） |
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| 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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| 关 键 词： | 航空发动机 分布式控制系统 自适应滑模控制 时延 不确定性 |
| 收稿时间： | 2015/11/20 0:00:00 |
Adaptive sliding mode control for uncertain aero-enginedistributed control system |
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| REN Litong,XIE Shousheng,WANG Lei,MIAO Zhuoguang,PENG Jingbo.Adaptive sliding mode control for uncertain aero-enginedistributed control system[J].Journal of Aerospace Power,2017,32(8):2032-2040. |
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| Authors: | REN Litong XIE Shousheng WANG Lei MIAO Zhuoguang PENG Jingbo |
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| Abstract: | With a focus on the aero-engine distributed control system with parameter perturbation and external disturbance,a robust adaptive sliding mode controller was designed under the condition of time-varying input delay and unknown disturbance upper bound.Firstly,based on the theory of predictive control and matrix singular value,an equivalent linear transformation was conducted for the original aero-engine discrete distributed control system,and a normal form model was obtained,making it easier to solve the sliding mode surface parameters.Secondly,with a given H∞ performance index,the sufficient condition for the asymptotical stability of sliding mode motion was deduced considering the influence of mismatched uncertainties.The sliding mode surface design method in linear matrix inequality (LMI) form was thus obtained.Finally,the adaptive law with disturbance estimation function was designed,and the adaptive sliding mode controller was proposed accordingly.Simulation results show that the proposed controller could reduce the impact of external disturbance on the system's dynamic performance effectively.Under the function of the considered uncertain factors,the system's sliding mode motion presented ideal H∞ performance.When the external disturbance intensity changed,the controller exhibited better robustness.The state convergence time was shorter than 0.8s,and there was no chattering phenomenon. |
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| Keywords: | aero-engine distributed control system adaptive sliding mode control time delay uncertainty |
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