发动机稳态与过渡态控制集成设计仿真验证

Design and simulation of aero-engine steady-state and transient-state control integration

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 issue of synthesizing steady-state and transient-state control laws for a turbofan engine was studied.Firstly,a number of steady-state point PI（proportional integral） controllers were designed using root locus analysis and time domain method from ground idle power to take-off power,and furthermore full flight envelope controllers were designed using interpolation method and corrected parameters.Secondly,the synthesis control system was acquired by integrating schedule-based transient control and steady-state control through max/min logic into which an anti wind-up module was added to cope with the influence of integrator wind-up.Finally,the synthesis control system was validated in software MATLAB/Simulink.The results indicate that the synthesis control system has the following advantages：（1） during steady-state,the anti-disturbance quality is good;（2） during transient-state,the response curve is flat;（3） the system uses a variety of restrictions effectively with both anti-windup and smooth switching functions.