涡扇发动机气路部件故障增益调度容错控制

Gain-Scheduling Fault-Tolerant Control for Gas Path Component Fault of Turbofan Engine

关键词:  航空发动机  气路部件故障  容错控制  增益调度  健康参数  部件线性化

Key words:  Aeroengine  Gas path component fault  Fault-tolerant control  Gain scheduling  Health parameters  Component linearization

摘要:

针对涡扇发动机气路部件故障导致控制性能下降甚至影响安全性的问题，提出了一种增益调度容错控制器设计方法。在全飞行包线内对发动机不同的工作点，基于部件线性化方法建立高精度的带健康参数的发动机线性化模型，并设计相应的卡尔曼滤波器构建气路部件故障诊断模块，估计出反映发动机气路部件故障程度的健康参数；针对不同工作点处正常状态和部件故障状态的线性化模型，分别设计一系列的鲁棒控制器，并根据调度参数和健康参数对发动机进行增益调度控制，以某型民用涡扇发动机为对象实现控制器的仿真验证。仿真结果表明：通过引入健康参数这一新的调度变量实现了增益调度容错控制，改善了原控制系统在气路部件发生故障导致部件流量和效率较大变化时的控制效果，保证了系统的稳定性；同时，在全飞行包线范围内有效地实现了气路部件故障下控制指令跟踪，达到了期望响应性能，控制误差、超调量和调节时间都很小，符合发动机控制系统技术要求。

Abstract:

Aiming at the problem that gas path component fault of turbofan engine leads to the decrease of control performance and even impacts the flight safety， a design method of gain-scheduling fault-tolerant controller is proposed. At different operating points of the engine in the full flight envelope， a component linearization method is used to establish high-precision linear engine models with health parameters， and corresponding Kalman filters are designed to construct a gas path component fault diagnosis module to estimate health parameters that reflect the degree of fault of engine gas path components.A series of robust controllers are designed for the linear models for normal and fault states at different operating points， and gain scheduling control is performed for the engine according to scheduling parameter and health parameters. Finally，the simulation of the controller was carried out with a certain type of civil turbofan engine. The simulation results show that the gain scheduling fault-tolerant control is realized by introducing the new scheduling variable of the health parameter， which improves the control effect of the original control system when the gas path components fault which caused a large change in the flow rate and efficiency of the component， and the stability of the system is ensured. Meanwhile， it effectively implements the control command tracking under the fault of gas path components achieving the desired response performance within full flight envelope， the control error， overshoot and adjustment time are very small， which meets the technical requirements of the engine control system.