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针对航空发动机传统单变量线性控制器min-max切换方法处理约束的不足,提出了单变量滑模控制器替换所有线性控制器的改进策略,并将该方法拓展为新切换逻辑下的多变量滑模控制结构。基于改进的单变量滑模控制器min-max结构,多变量控制策略中加入了多变量滑模主控制器和新的切换逻辑,充分利用发动机的所有控制量,克服了传统方法的保守性,进一步提高发动机约束下的动态性能。对稳态时工作的控制器进行了理论分析,建立了多变量控制器实现精确跟踪的充要条件。仿真结果表明,多变量控制方法在更苛刻的约束条件下能够实现跟踪任务,而且提高了推力跟踪的快速性,调节时间从1.91s缩短到1.54s,同时降低了稳态时的油耗。
In order to deal with the limitation of min-max switching method of traditional univariate linear controller of aeroengine, an improved strategy for replacing all linear controllers with a single variable sliding mode controller is proposed. The method is extended to the multivariable sliding mode under the new switching logic Mold control structure. Based on the improved min-max structure of the single variable sliding mode controller, a multivariable sliding mode controller and a new switching logic are added into the multivariable control strategy to make full use of all the control quantities of the engine and overcome the conservativeness of the traditional method. Further improve the dynamic performance under engine constraints. The steady-state working controller is analyzed theoretically, and the necessary and sufficient condition for multivariable controller to realize accurate tracking is established. The simulation results show that the multivariable control method can achieve the tracking task under the more restrictive constraints and improve the thrust tracking speed. The adjustment time is shortened from 1.91s to 1.54s and the fuel consumption at steady state is reduced.