Continuously variable Mach number control method at supersonic speed and constant total pressure in large open jet wind tunnel

Abstract

The present invention disclosed a large -scale opening of the high -speed consecutive Mapo control method.This control method adopts a composite control strategy of total voltage feedback ‑ feedback, and feedback controls the cluster of the wind tunnel pressure regulating valve regulating characteristic curve. According to the real -time nozzle noodles and gas source pressure during the operating process of the wind tunnel, calculate the calculation.The amount of compensation for the displacement of the pressure regulating valve required for the changes in the noodle surface and the pressure of the gas source, eliminating the greater interference caused by the total pressure of the sperm type and the decrease in gas source pressure; the feedback control is controlled by incremental PID,According to the real -time feedback of the total pressure, the pressure regulating valve displacement is constantly regulated to achieve the total pressure closed -loop control and suppress random interference during the operation of the wind tunnel.This control method can effectively eliminate or suppress large -scale open -flow wind tunnel supersonic continuous change of the Maghi number test. During the interference caused by the changes in the total pressure control of the total pressure control of the total pressure control, the accuracy, fastness and speed of total pressure control have been improved.Robber.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel tests, and in particular relates to a control method for continuously variable Mach number at supersonic constant total pressure in a large-scale open jet wind tunnel. Background technique [0002] During the supersonic continuous variable Mach number test in a large-scale open jet wind tunnel, it is difficult to control the total pressure in the stable section, and there are two external disturbances in the control: one is the total pressure in the stable section caused by the change of the wind tunnel nozzle profile when the Mach number is continuously changed. large fluctuations in pressure. Second, the rapid drop in air source pressure during the wind tunnel test operation causes a decrease in the intake flow rate of the pressure regulating valve, resulting in a rapid drop in the total pressure in the stable section. From the point of view of control theory, these two kinds of disturbance...

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Problems solved by technology

[0002] During the supersonic continuous variable Mach number test in a large-scale open jet wind tunnel, it is difficult to control the total pressure in the stable section, and there are two external disturbances in the control: one is the total pressure in the stable section caused by the change of the wind tunnel nozzle profile when the Mach number is continuously changed. large fluctuations in pressure

The second is the rapid drop of air source pressure during wind tunnel test operation, resulting in a decrease in the intake flow of the pressure regulating valve, resulting in a rapid drop in the total pressure in the stable section

The traditional closed-loop control strategy of total pressure feedback in the stable section can effectively suppress step disturbances, but the anti-disturbance ability to the above two kinds of slope disturbances is poor, and there is a large steady-state error in the total pressure control of the stable section

Although the classic PID control can increase the integral coefficient to reduce the steady-state error caused by the slope disturbance, the increase of the integral coefficient is easy to cause oscillation and divergence of the total pressure control of the assembly. Security Risk

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