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针对非对称受损的常规布局飞机,对其自适应控制设计方法与适用条件进行了研究.建立了非对称结构受损飞机的非线性模型,详细讨论了模型的线性化过程以及受损造成的纵、横向间动态耦合项;结合常规布局非对称结构受损飞机的物理特性,对多变量模型参考自适应控制器设计的关键条件:关联矩阵和高频增益矩阵顺序主子式符号的不变性做出了证明,确立了该方法在非对称结构受损飞机上应用的理论可行性;通过仿真验证了MRAC(Model Reference Adaptive Control)方法对非对称结构受损飞机控制的有效性.
Aiming at the asymmetric damaged conventional layout aircraft, the adaptive control design method and its applicable conditions are studied.The nonlinear model of the damaged aircraft with asymmetric structure is established, and the linearization process and the damage caused by the model are discussed in detail The dynamic coupling between longitudinal and transverse directions is proposed. Combining with the physical characteristics of the damaged aircraft with asymmetric structure, the invariance of the principal subordinate symbols to the multivariable model reference adaptive controller design is given: the correlation matrix and the order of the high frequency gain matrices It proves that the method is feasible for the application of the proposed method to the damaged aircraft with asymmetric structure. The effectiveness of MRAC (Model Reference Adaptive Control) method for the control of damaged aircraft with asymmetric structure is verified by simulation.