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研究了某型涡扇发动机全飞行包线稳态与过渡态控制集成设计问题.首先利用根轨迹分析法和时域分析法设计了从慢车状态到最大状态的多个比例积分(PI)设定点控制器,并利用增益调参和换算参数得到了全飞行包线的稳态控制器参数.然后将加减速控制计划与稳态控制通过max/min逻辑进行集成,考虑了抗积分饱和功能及设计了相应的抗积分饱和模块,最后得到的集成控制系统在软件MATLAB/Simulink下进行了仿真验证.仿真结果表明集成控制系统稳态时抗扰动性能良好,过渡过程中曲线平滑,有效利用了各种限制条件还兼有抗积分饱和功能并且能进行平滑切换.
The integration design of steady-state and transition-state control of a full-scale turbofan engine was studied.The multiple proportional integral (PI) settings from the idle state to the maximum state were designed by root locus analysis and time domain analysis Point controller and the parameters of steady-state controller of full flight envelope are obtained by using gain tuning and scaling parameters.At the same time, the acceleration / deceleration control plan and steady-state control are integrated by max / min logic, the anti-integration function and The corresponding anti-integral saturation module is designed and the integrated control system is finally verified by software MATLAB / Simulink.The simulation results show that the integrated control system has good anti-disturbance performance under steady state and smooth transition curve, Kinds of restrictions also have anti-integral function and smooth switching.