民用涡扇发动机预测控制器设计

Design of Model Predictive Controller for Commercial Turbofan Engine

对一定包线范围内的稳态预测控制器和加速减速过渡态控制器设计展开研究。针对某大涵道比民用涡扇发动机,根据发动机进口参数的相对变化指标对控制区域进行划分,以标称点处发动机线性模型为对象设计了相应的预测控制器,利用提出的多层参数调度方案实现了不同飞行条件及不同发动机状态下预测控制器参数的自适应调整。仿真结果表明:所设计的发动机预测控制系统在控制区域内的设计点和非设计点均具有良好的性能,为全包线设计提供了有效方法。

A novel design of aeroengine model predictive controller for steady state as well as acceleration/deceleration transition state within a certain flight envelop was studied.Aiming at a high bypass ratio commercial turbofan engine,the control domain was divided according to the relative change of the engine inlet parameters.A series of predictive controllers based on linear models of different nominal points were designed.An adaptive predictive controller under different flight conditions and engine states was achieved by a proposed multilayer parameters scheduling program.Simulation results show that the designed predictive control system at the design and off-design points of the control domain is of good performance,which provides an effective approach for the design of the whole envelop controller.