航空发动机的多变量滑模控制方法研究

发布时间：2018-06-30 00:43

本文选题：航空发动机 + 滑模控制　；参考：《清华大学》2015年硕士论文

【摘要】：航空发动机系统是一个复杂的非线性、强耦合多变量系统,要让其合理有效地工作,需要采用现代的先进控制理论和方法。滑模变结构控制是一种特殊的非线性控制方法,其最大的优点是在滑模面上对系统参数和外界干扰等不确定因素具有较强的鲁棒性,因而非常适用于航空发动机控制系统。论文以NASA的民用涡扇发动机模型CMAPSS-1和CMAPSS-40k为研究对象,对航空发动机多变量滑模控制方法进行了较全面的研究,在Matlab/Simulink环境下对各种滑模控制方法进行了设计点附近的线性仿真,并应用LPV建模方法对非线性动态过程进行了相应的仿真验证。论文首先研究了带有等速、指数和幂次趋近律的常规滑模控制方法中控制参数大小对系统性能的影响,比较了采用不同趋近律对滑模控制的影响,并用趋近律对全程快速非奇异Terminal滑模控制进行优化。论文随后分析了用模糊滑模方法、自适应滑模方法以及结合自适应模糊的滑模智能方法设计滑模控制器的过程,通过理论推导对其稳定性进行了证明,并通过仿真对比不同滑模智能控制方法的优缺点和适用性,得到系统综合控制效果最优化的自适应模糊控制方法。最后,论文研究了更具有工程实际意义的航空发动机滑模限制控制方法,采用基于混合2H/H?设计方法的滑模限制控制,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,同时也确保了系统具有最优的响应效果和鲁棒性。通过与基于线性调节器的限制控制对比,进一步验证了滑模限制控制的优点;将滑模智能控制方法与限制控制结合,通过在线性和非线性模型上仿真,得到了控制效果最优的自适应模糊滑模限制控制方法。
[Abstract]:The aero-engine system is a complex nonlinear and strongly coupled multivariable system. Modern advanced control theories and methods are needed to make it work reasonably and effectively. Sliding mode variable structure control (VSC) is a special nonlinear control method. Its greatest advantage is that it is robust to uncertain factors such as system parameters and external disturbances on the sliding mode surface, so it is very suitable for aero-engine control systems. Taking the civil turbofan engine models CMAPSS-1 and CMAPSS-40k of NASA as the research objects, the multivariable sliding mode control method of aeroengine is studied in this paper. The linear simulation of various sliding mode control methods near the design point is carried out in Matlab / Simulink environment. The LPV modeling method is used to verify the nonlinear dynamic process. In this paper, the influence of control parameters on the performance of conventional sliding mode control methods with constant velocity, exponential and power law is studied, and the effects of different convergence laws on sliding mode control are compared. The fast nonsingular terminal sliding mode control is optimized with approach law. Then, the process of designing sliding mode controller with fuzzy sliding mode method, adaptive sliding mode method and adaptive fuzzy sliding mode intelligent method is analyzed, and its stability is proved by theoretical derivation. By comparing the advantages and disadvantages and applicability of different sliding mode intelligent control methods, an adaptive fuzzy control method with optimal comprehensive control effect is obtained. Finally, the thesis studies the sliding mode limited control method of aero-engine, which is of engineering significance, and adopts the hybrid 2H / H? The design of sliding mode control not only ensures that the key variables of the system remain below the limit value during the transition period, but also ensures the optimal response effect and robustness of the system. The advantages of sliding mode limited control are further verified by comparing with the limited control based on linear regulator, the intelligent sliding mode control method is combined with the limited control method, and the simulation is carried out on the linear and nonlinear models. An adaptive fuzzy sliding mode constrained control method with optimal control effect is obtained.
【学位授予单位】：清华大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V233.7

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