本文選題：航空發(fā)動機 + 滑�？刂���； 參考：《清華大學》2015年碩士論文

【摘要】：航空發(fā)動機系統(tǒng)是一個復雜的非線性、強耦合多變量系統(tǒng),要讓其合理有效地工作,需要采用現(xiàn)代的先進控制理論和方法。滑模變結構控制是一種特殊的非線性控制方法,其最大的優(yōu)點是在滑模面上對系統(tǒng)參數(shù)和外界干擾等不確定因素具有較強的魯棒性,因而非常適用于航空發(fā)動機控制系統(tǒng)。論文以NASA的民用渦扇發(fā)動機模型CMAPSS-1和CMAPSS-40k為研究對象,對航空發(fā)動機多變量滑�？刂品椒ㄟM行了較全面的研究,在Matlab/Simulink環(huán)境下對各種滑模控制方法進行了設計點附近的線性仿真,并應用LPV建模方法對非線性動態(tài)過程進行了相應的仿真驗證。論文首先研究了帶有等速、指數(shù)和冪次趨近律的常規(guī)滑�？刂品椒ㄖ锌刂茀�(shù)大小對系統(tǒng)性能的影響,比較了采用不同趨近律對滑�？刂频挠绊�,并用趨近律對全程快速非奇異Terminal滑�？刂七M行優(yōu)化。論文隨后分析了用模糊滑模方法、自適應滑模方法以及結合自適應模糊的滑模智能方法設計滑模控制器的過程,通過理論推導對其穩(wěn)定性進行了證明,并通過仿真對比不同滑模智能控制方法的優(yōu)缺點和適用性,得到系統(tǒng)綜合控制效果最優(yōu)化的自適應模糊控制方法。最后,論文研究了更具有工程實際意義的航空發(fā)動機滑模限制控制方法,采用基于混合2H/H?設計方法的滑模限制控制,不僅保證了系統(tǒng)的關鍵變量在過渡態(tài)期間始終維持在限制值以下,同時也確保了系統(tǒng)具有最優(yōu)的響應效果和魯棒性。通過與基于線性調節(jié)器的限制控制對比,進一步驗證了滑模限制控制的優(yōu)點;將滑模智能控制方法與限制控制結合,通過在線性和非線性模型上仿真,得到了控制效果最優(yōu)的自適應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.
【學位授予單位】：清華大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：V233.7

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