超声速进气道正激波位置动态辨识与控制方法研究

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

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。

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.