Large-flow high-stability Mach number wind tunnel rapid adjusting system and method based on temporary charging air source

Abstract

The invention provides a large-flow high-stability Mach number wind tunnel rapid adjusting system and method based on a temporary charging air source. The large-flow high-stability Mach number wind tunnel rapid adjusting system structurally comprises a temporary charging air source, a main valve, an auxiliary valve, a spraying pipe, a pressure sensor, a Mach number sensor and a control unit, and the auxiliary valve has the faster small-flow adjusting capacity and is connected with the main valve in parallel. The method comprises the following steps: (1) on the basis of 50% opening degree of an auxiliary valve, carrying out main valve manual adjustment on a characteristic Mach number point in a wind tunnel capability range to obtain a main valve opening degree and air source pressure relation curve cluster under a corresponding Mach number; (2) according to the instruction Mach number and the current air source pressure, obtaining the opening degree of a main valve through two-dimensional linear interpolation; and (3) carrying out closed-loop PID adjustment of the instruction Mach number by using the auxiliary valve, and maintaining the outlet Mach number. According to the invention, a composite control strategy of main valve feedforward and auxiliary valve closed-loop PID is adopted, and the problem that an outlet Mach number is not easy to stabilize due to continuous decrease of gas source pressure, poor repeatability of a main valve, strong nonlinearity and slow adjusting speed in a wind tunnel test is solved.

Description

technical field [0001] The invention relates to a large-flow high-stable Mach number wind tunnel rapid adjustment system and method based on a temporary flushing gas source, belonging to the field of wind tunnel test measurement and control in the aerospace industry. Background technique [0002] The wind tunnel is one of the most commonly used aerodynamic experimental equipment in the aerospace industry. It artificially generates and controls the airflow to simulate the flow of air around the aircraft or entity, and to measure the effect of the airflow on the entity. And a tube-like experimental device for observing physical phenomena. Wind tunnel test is an important means to obtain aircraft aerodynamic data, measure aircraft shape design layout and evaluate flight performance. For the jet-type wind tunnel commonly used in the aerospace industry, the wind tunnel test data is significantly affected by the accuracy of the exit Mach number, so the exit Mach number is one of ...

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Problems solved by technology

[0006] The present invention proposes a large-flow, high-stable Mach number wind tunnel rapid adjustment system and method based on a temporary flushing gas source. Realize the rapid adjustment of the outlet Mach number, and can maintain it stably for a long time, overcoming the outlet Mach caused by the temporary flushing air source pressure drop in the temporary flushing wind tunnel system, poor repeatability of the main valve, strong nonlinearity, and slow adjustment speed The problem of slow and unstable data adjustment

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