典型文献
Vector deflection stability control of aero-engine based on linear active disturbance rejection
文献摘要：
Aimed at the problem of instability in engine control caused by vector deflection in experiment of turbofan engines with Axisymmetric Vectoring Exhaust Nozzle(AVEN),a vector deflection stability control method of aero-engine based on Linear Active Disturbance Rejection Control(LADRC)is proposed.Firstly,based on CFD numerical simulation,aerodynamic perfor-mance model of AVEN is established,and the aerodynamic load change rule of the nozzle throat area actuator during vector deflection is revealed.Subsequently,the integrated model of AVEN/-turbofan engine is established by Simulink/AMESim co-simulation.Finally,the nozzle throat area control loop based on LADRC is designed.The simulation results show that the integrated model can reflect the influence of vector deflection on the stability of the control system.The accuracy comparison between the fan rotor speed and the test data during vector deflection is larger than 1％,indicating a high degree of confidence.Compared with the conventional PID control,the designed LADRC control loop reduces the speed of the low-pressure rotor during vector deflection by 70％,which effectively improves the control stability of the vector deflection.Meanwhile,the fuel flow ratechange during the vector deflection process is smaller and more economical,which provides an important reference for engineering applications.
文献关键词：
中图分类号：
作者姓名：
Changpeng CAI;Yerong PENG;Qiangang ZHENG;Haibo ZHANG
作者机构：
College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China
文献出处：
引用格式：
[1]Changpeng CAI;Yerong PENG;Qiangang ZHENG;Haibo ZHANG-.Vector deflection stability control of aero-engine based on linear active disturbance rejection)[J].中国航空学报（英文版）,2022(08):221-235
A类：
turbofan,Vectoring,AVEN,ratechange
B类：
deflection,control,linear,active,disturbance,rejection,Aimed,problem,instability,caused,by,vector,experiment,engines,Axisymmetric,Exhaust,Nozzle,method,Linear,Active,Disturbance,Rejection,Control,LADRC,proposed,Firstly,CFD,numerical,simulation,aerodynamic,perfor,mance,model,established,load,rule,nozzle,throat,area,actuator,during,revealed,Subsequently,integrated,Simulink,AMESim,Finally,loop,designed,results,show,that,can,reflect,influence,system,accuracy,comparison,between,rotor,speed,test,data,larger,than,indicating,high,degree,confidence,Compared,conventional,PID,reduces,pressure,which,effectively,improves,Meanwhile,fuel,flow,process,smaller,more,economical,provides,important,reference,engineering,applications
AB值：
0.462526
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