基于滑模控制方法的航空发动机限制控制研究  

Research on Limit Management with Sliding Mode Control in Aero-Engine

作　　者：孙晖[1,2] 刘尚明[1] 

机构地区：[1]清华大学热能工程系热科学与动力工程教育部重点实验室,北京100084 [2]中国航空工业集团公司航空动力控制系统研究所,无锡214063

出　　处：《热力透平》2016年第2期132-137,143,共7页Thermal Turbine

摘　　要：考虑到对航空发动机工作安全性和持久性的要求,采用基于滑模控制的航空发动机限制控制,将系统关键变量维持在允许的限制范围内。利用混合H_2/H_∞方法设计低选-高选滑模限制控制器,在CMAPSS线性化模型上仿真研究,并与基于线性调节器的限制控制方法对比分析。结果表明,滑模限制控制方法不仅保证了系统的关键变量在过渡态期间始终维持在限制值以下,同时还确保了系统具有最优的响应效果和鲁棒性。According to the demand of safety and durability in aero-engine, the limit management with sliding mode control was studied to maintain critical engine variables within permissible constraints. In this research, an H2/H∞ sliding coefficient synthesis method was used to design the max-min SMC approach, and the simtllations were performed using the CMAPSS linear engine model. Compared with limit management with linear regulators, the advantages of limit management with SMC were verified. The analysis shows that aero-engine limit management with SMC constrains system can not only maintain outputs within limiting value, but also guarantee the system with good response effect and strong robustness.

关 键 词：航空发动机 滑模控制 限制控制 混合H2/H∞设计方法 线性调节器 

分 类 号：V233.7[航空宇航科学与技术—航空宇航推进理论与工程]