PI decoupling control method of turboprop engine based on model reference adaptive compensation
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摘要:
针对常规的涡桨发动机PI解耦控制方法在全包线内鲁棒性不足的问题，提出了一种基于模型参考自适应补偿的PI解耦控制方法。基于涡桨发动机转子动力学及阶次特性，提出了一种涡桨发动机传递函数矩阵获取方法。并以此为基础，结合零极点相消法，分别设计了解耦环节与双回路PI控制器。通过建立闭环系统的期望状态空间方程，设计模型参考自适应补偿以有效提升控制器的鲁棒性能。此外，为了进一步改善控制方法的动态跟踪性能，采用基于自适应速率协方差调节的快速自适应律。基于涡桨发动机非线性仿真模型开展了控制方法仿真验证。结果表明：在不同的飞行包线点，相比于常规PI解耦控制器，采用基于模型参考自适应补偿的PI解耦控制方法可使燃气涡轮转速的最大调节时间缩短15%左右，超调量减少90%以上，动力涡轮转速的最大超调或下垂量减小60%以上，具有更高品质的动态控制效果、更优越的鲁棒性能与抗扰能力。
Abstract:In view of the problem that the conventional PI decoupling control method of turboprop engine has insufficient robustness in the whole envelope, a PI decoupling control method based on model reference adaptive compensation was proposed. Based on the rotor dynamics and order characteristics of turboprop engine, a method to obtain the transfer function matrix of turboprop engine was also proposed. On this basis, combined with the zero pole elimination method, the decoupling link and double loop PI controller were designed respectively. By establishing the expected state space equation of the closed-loop system, a model reference adaptive compensation method was designed to effectively improve the robust performance of the controller. In addition, in order to further improve the dynamic tracking performance of the control method, a fast adaptive law based on adaptive rate covariance adjustment was adopted. Based on the nonlinear simulation model of turboprop engine, simulation verification of the control method was carried out. The results showed that at different flight envelope points, compared with the conventional PI decoupling controller, the PI decoupling control method based on model reference adaptive compensation can shorten the maximum regulation time of gas turbine speed by about 15%, reduce the overshoot by more than 90%, and cut down the maximum overshoot or droop of power turbine speed by more than 60%. It exhibited higher dynamic control effect, superior robustness and disturbance rejection ability.
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图 2 线性模型与非线性模型相应对比图
Figure 2. Corresponding comparison diagram of linear model and nonlinear model
图 4 基于模型参考自适应的PI解耦控制结构图
Figure 4. Structure diagram of PI decoupling control based on model reference adaptive compensation
图 7 仿真点1（设计点）发动机阶跃响应图
Figure 7. Engine’s step response diagram of operating point 1 （design point）
图 9 变飞行工况下的非线性模型仿真1
Figure 9. Nonlinear simulation 1 of nonlinear model under variable flight conditions
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