超声速进气道正激波位置动态辨识与控制方法研究 *

推进技术 ›› 2018, Vol. 39 ›› Issue (4): 888-897.

超声速进气道正激波位置动态辨识与控制方法研究 *

杜瑶,张海波

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016

发布日期:2021-08-15
作者简介:杜瑶，男，硕士生，研究领域为航空发动机建模与仿真。E-mail: nuaaduyao@126.com 通讯作者:张海波，男，教授，研究领域为航空发动机建模及控制。
基金资助:
中央高校科研基本业务费(NZ2016103)；国家自然科学基金(51576096)。

Research on Dynamic Identification and Control Method of Normal Shock Position of Supersonic Inlet

Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing 210016，China and Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 为了实现超声速进气道闭环控制，对基于放气流量调节的进气道正激波位置动态辨识与控制问题进行了研究。基于超声速进气道二维CFD模型，探究了放气流量、来流压力、温度、马赫数对正激波位置的动、静态影响，并对其传递函数进行了辨识。以此为基础，在Matlab Simulink环境下，针对正激波位置控制设计了一种自抗扰控制律(ADRC)。仿真结果表明，所设计闭环系统响应时间短，超调量小，相比于常规PI控制可更有效地抑制来流干扰。

关键词: 进气道；正激波；来流干扰；闭环控制；自抗扰控制

Abstract: In order to come true the closed-loop control of a supersonic aircraft inlet， the dynamic identification and control of the positive shock in the inlet is studied， based on bleed air flow regulation under supersonic conditions. Using a two-dimensional CFD model of the inlet， the dynamic and static effects of bleed air flow， upstream pressure， upstream temperature and Mach number on the position of norm shock were investigated. Those transfer functions between the norm shock position and the above influent factors were identified. Based on this， an active disturbance rejection controller (ADRC) is designed for the positive shock position control in Matlab Simulink environment. The simulation results show that the designed closed-loop system has a short response time and a small overshoot， compared to conventional PI control， which can reject upstream disturbances more effectively.

Key words: Inlet；Normal shock wave；Upstream disturbances；Closed-loop control；Active disturbance rejection controller

杜瑶,张海波. 超声速进气道正激波位置动态辨识与控制方法研究 *[J]. 推进技术, 2018, 39(4): 888-897.

DU Yao,ZHANG Hai-bo. Research on Dynamic Identification and Control Method of Normal Shock Position of Supersonic Inlet[J]. Journal of Propulsion Technology, 2018, 39(4): 888-897.

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