Design And Implementation On Wind Tunnel Transonic Flow Field Control System

The wind tunnel experiment is an indispensable part of the development of the aircraft.It not only plays an important role in the research and development of aviation and aerospace engineering.With the development of industrial aerodynamics,it is indispensable in the fields of transportation,housing construction,and wind energy utilization.The most important indicator of a wind tunnel system is the Mach number.Increasing the accuracy of Mach number control has always been the pursuit and goal of wind tunnel workers,and it can also bring more accurate test data to aircraft design.This srticle takes the FL-60 wind tunnel flow field control system as the research object.Firstly,based on the detailed analysis of the structure,design index and measurement and control system of the DC ejector sub-supersonic supersonic wind tunnel system,the hardware design schemes of the pressure control valve hydraulic system and the grid finger mechanism system are independently controlled.Second,the wind tunnel in the transonic flow field control mode is divided into the main regulator valve control mode,the main regulator valve plus grid finger control mode(Mach number precision control mode),The strategy and flow of the two control modes are designed in detail.In the main regulator control mode,a suitable Mach pressure compensation controller is designed according to the characteristics of the regulator valve obtained by the test;Then,according to the classic PID controller,the initial controller parameters are determined,and the parameters of the Mach number controller are determined through wind tunnel experiments.On the basis of the main pressure regulation control mode,the inner ring of the control position of the grid finger is increased,and the outer ring is the total pressure/Mach number control.The Mach number controller is designed based on the theoretical and experimental results.Finally,taking the Mach number precise control mode as an example,detailed test methods and debugging schemes are given,and the debugging results are recorded and analyzed.The results show that the maximum fluctuation of the flow field Mach number under the main pressure regulating valve plus grid finger control combined control mode reaches the national military standard qualification index,Some Mach numbers reach advanced indicators.The FL-60 wind tunnel gate refers to the Mach number precision control system with engineering application conditions.