摘要
为进一步提高航空发动机燃油控制回路的控制性能,使其达到数控系统性能指标要求,针对发动机的特性,从其控制系统的实际运用角度出发,开发出适用于其燃油控制回路PI控制器的根轨迹参数设计方法。该方法采用根轨迹图并结合控制性能指标要求确定了闭环主导极点的期望区域,在根轨迹图上放置极点和零点,移动闭环主导极点到期望区域内以确定满足性能指标要求的PI控制器参数。通过仿真试验发现,采用根轨迹法所设计的燃油控制回路PI控制器参数不仅能达到数控系统性能指标要求,所设计PI控制器的控制品质还明显优于零极点对消法。
In order to improve the control performance of aeroengine fuel control loop, and make it fulfill the performance indices,according to the properties of aeroengine and actual application of aeroengine digital electronic control system, the root locus method applied to PI controller design of aeroengine fuel loop control was developed. Combining root locus diagram with control performance indices, the expected zone of closed loop dominant pole was determined. By putting pole and zero on the root locus diagram, and moving the closed loop dominant pole to the expected zone, the PI controller fulfilling performance indices was got. The result of simulation demonstrates that the control performance of the PI controller designed by the root locus fulfills the performance indices is apparently better than the control quality of the PI controller designed by pole-zero cancellation.
出处
《航空发动机》
2016年第4期17-20,共4页
Aeroengine
基金
国家重大基础研究项目资助
