摘要
针对航空发动机的滑模控制性能优化问题,以多输入多输出的CMAPSS-40k民用涡扇发动机线性模型为控制对象,对使用等速、指数和幂次趋近律的滑模控制进行仿真,比较不同趋近律对滑模控制效果的优化作用。在此基础上,利用指数趋近律对全局快速Terminal滑模控制和全局快速非奇异Terminal滑模控制进行优化,并比较两者的控制性能。仿真结果表明,改进后的全局快速非奇异Terminal滑模控制系统具有更快的响应和更强的鲁棒性。
Aiming at optimizing performance of aero-engine sliding mode controller（ SMC）,the linear model CMAPSS-40 k of a multiinput multi-output（ MIMO） turbofan engine was used for simulation. Constant speed reaching law,exponential and power reaching law were proposed and optimizing effect of different reaching laws was compared. On this basis,exponential reaching law was designed for global fast terminal SMC and global fast non-singular terminal SMC. Simulation results show that the modified global fast non-singular terminal SMC controller has shorter response time and better robustness.
出处
《燃气轮机技术》
2015年第1期1-6,共6页
Gas Turbine Technology
