基于PID趋近律的航空发动机滑模变结构控制  

Aero Engine Sliding Model Variable Structure Controller Based on PID Reaching Law

作　　者：何秀然[1] 谢寿生[1] 邹仕军[2] 孙冬[1] 

机构地区：[1]空军工程大学工程学院,陕西西安710038 [2]沈阳飞机公司军代室,辽宁沈阳110021

出　　处：《空军工程大学学报（自然科学版）》2009年第3期15-20,共6页Journal of Air Force Engineering University(Natural Science Edition)

摘　　要：研究了一种自调节趋近律的滑模变结构控制器,以切换函数s作为偏差,趋近速度由一个PID控制器调节,目的是使到达滑模面的穿越速度最小从而减少抖振,同时使到达滑模面时间最短。根据航空发动机稳态数学模型,设计其滑模变结构控制律,构建了基于PXI总线的发动机滑模控制平台。通过半实物实验结果证明,该控制器响应速度快,高频抖振很小,具有很强的鲁棒性能和跟踪性能。A sliding model variable structure controller with auto - adjusted reaching law is researched in this paper. In the research, switch function s is taken as an error and reaching speed is adjusted by PID controUer, with the intention of minimizing the traversing speed when arriving at the sliding model surface to reduce chattering and optimize the arrival time. According to the aero engine steady mathematic model, the sliding model variable struc- ture control law is designed, the aero engine＇s sliding model controller based on PXI bus is constructed. The part - actual simulation results show that the controller is of swift response, tiny high - frequency chattering and is strong in robustness and tracking.

关 键 词：航空发动机 滑模变结构控制 趋近律 PID控制 PXI总线 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]