Recent research progress on airbreathing aero-engine control algorithm  

作　　者：Chengkun Lv Juntao Chang Wen Bao Daren Yu 

机构地区：[1]Harbin Institute of Technology,Heilongjiang,150001,China

出　　处：《Propulsion and Power Research》2022年第1期1-57,共57页推进与动力（英文）

基　　金：This research work is supported by the National Science and Technology Major Project(2017-V-0004-0054);the National Natural Science Foundation of China(Grant No.52125603);the National Natural Science Foundation of China(Grant No.11972139);the Fundamental Research Funds for the Central Universities(HIT.BRET.2021006 and FRFCU5710094620).

摘　　要：Airbreathing aero-engines are regarded as excellent propulsion devices from ground takeoff to hypersonic flight,and require control systems to ensure their efficient and safe operation.Therefore,the present paper aims to provide a summary report of recent research progress on airbreathing aero-engine control to help researchers working on this topic.First,five control problems of airbreathing aero-engines are classified:uncertainty problem,multiobjective and multivariable control,fault-tolerant control,distributed control system,and airframe/propulsion integrated control system.Subsequently,the research progress of aircraft gas turbine engine modelling,linear control,nonlinear control,and intelligent control is reviewed,and the advantages and disadvantages of various advanced control algorithms in aircraft gas turbine engines is discussed.Third,several typical hypersonic flight tests are investigated,and the modelling and control issues of dual-mode scramjet are examined.Fourth,modelling,mode transition control and thrust pinch control for turbine-based combined cycle engines are introduced.Followed,significant hypersonic airframe/propulsion integrated system control is analysed.Finally,the study provides specific control research topics that require attention on airbreathing aero-engines.

关 键 词：Airbreathing aeroengine Control Aircraft gas turbine engine Dual-mode scramjet Combined cycle engine Hypersonic airframe/propulsion integrated system 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]