航空科学技术2024，Vol.35Issue(12)：78-86,9.DOI:10.19452/j.issn1007-5453.2024.12.010
飞发一体化架构下航空发动机控制裕度定义及评估准则研究
Research on the Definition and Evaluation Criteria of Aeroengine Control Margin under the Integrated Flight-Propulsion Architecture
摘要
Abstract
In response to the difficulty of traditional margin evaluation standards to intuitively reflect the coupling problem of aircraft disturbance on aeroengine control,research on aeroengine control margin and corresponding evaluation criteria is carried out under the framework of integrated flight-propulsion architecture.A novel method for defining aeroengine control margin and evaluation criteria is proposed based on a control theory called geometric design method that can improve control performance using geometric methods in a finite frequency domain.This includes constructing a controller solution method that meets the required control margin,evaluating and comparing control margins of different controllers,and evaluating control margins of fixed structure controllers.Taking a certain type of turbine-based combined cycle(TBCC)engine as the research object,under the typical subsonic cruise condition,the controller designed based on geometric design method can achieve 99.61%of the control margin theoretical limit.The simulation results based on the TBCC component level model show that compared to the traditional proportional integral(PI)controller,the thrust control margin and comprehensive control margin of the controller designed based on geometric design method have increased by 7.3%and 5.9%,respectively,verifying the effectiveness of the defined control margin and its evaluation criteria in solving the coupling problem of integrated flight-propulsion control.关键词
飞发一体化/涡轮基组合动力/控制裕度/几何设计法/评估准则Key words
integrated flight-propulsion/turbine-based combined cycle/control margin/geometric design method/evaluation criteria分类
航空航天引用本文复制引用
陈佳杰,王继强,张海波,陈新民,牛伟..飞发一体化架构下航空发动机控制裕度定义及评估准则研究[J].航空科学技术,2024,35(12):78-86,9.基金项目
航空科学基金(201919052001) Aeronautical Science Foundation of China(201919052001) （201919052001）
