基于LMI的滑模控制在航空发动机中的应用
针对航空发动机运行过程中存在不确定性和稳定性问题,运用状态空间模型理论与线性矩阵不等式LMI相结合的方法设计了控制器,改善了航空发动机的控制性能.以某型涡扇发动机为控制对象,基于LMI对普通终端滑模变结构控制进行了优化设计,在滑模超平面设计中引入了动态补偿器,采用改进的幂次趋近律,对该动态系统进行了性能仿真验证.结果表明,本文提出的方法较之普通终端滑模变结构控制对系统性能有较大改善,不仅使系统主供油量变化率、尾喷口面积变化率等的控制更为平稳,且保证了系统鲁棒性和稳定性....
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| Published in | 计算机工程与科学 Vol. 36; no. 6; pp. 1198 - 1203 |
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| Main Author | |
| Format | Journal Article |
| Language | Chinese |
| Published |
湘潭大学信息工程学院,湖南湘潭,411105
2014
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| Subjects | |
| Online Access | Get full text |
| ISSN | 1007-130X |
| DOI | 10.3969/j.issn.1007-130X.2014.06.032 |
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| Summary: | 针对航空发动机运行过程中存在不确定性和稳定性问题,运用状态空间模型理论与线性矩阵不等式LMI相结合的方法设计了控制器,改善了航空发动机的控制性能.以某型涡扇发动机为控制对象,基于LMI对普通终端滑模变结构控制进行了优化设计,在滑模超平面设计中引入了动态补偿器,采用改进的幂次趋近律,对该动态系统进行了性能仿真验证.结果表明,本文提出的方法较之普通终端滑模变结构控制对系统性能有较大改善,不仅使系统主供油量变化率、尾喷口面积变化率等的控制更为平稳,且保证了系统鲁棒性和稳定性. |
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| Bibliography: | linear matrix inequality ; aero engine ; terminal sliding mode control ; dynamic compensator A new method,combined with the state-space model theory and the linear matrix inequality （LMI）,is applied to design a controller to improve the control performance of the aero engine for the sake of studying its uncertainty and instability during the actual operation.Taking the turbojet engine model as the control object,a dynamic compensator is introduced to improve the performance of aero-engine system through the optimal design of the terminal sliding mode control on the basis of the LMI.Furthermore,the improved power rate reaching law is used to validate the performance simulation of the dynamic system.It is shown that the proposed method not only smoothes the variance ratio of fuel and nozzle outlet area,but also holds the stable and robustness of the system.Our results based on LMI are better than the general terminal sliding mode control for the aero engine. 43-1258/TP HUANG Hui-xian,LI Yan,ZHUANG Xuan,REN Ke-ming |
| ISSN: | 1007-130X |
| DOI: | 10.3969/j.issn.1007-130X.2014.06.032 |