High-precision temporary punching type injecting transonic speed wind tunnel flow field control structure

Abstract

The invention relates to a high-precision temporary punching type injecting transonic speed wind tunnel flow field control structure and a method. According to the control structure, a wind tunnel flow field is decomposed into a main injection pressure control portion and a total pressure-static pressure control portion, and the control structure is mainly composed of such three modules as a set value calculation model, a main injection controller and a flow field controller. In the main injection pressure control portion, a main pressure regulating valve is adopted to control the main injection pressure. In the total pressure-static pressure control portion, the total pressure and the static pressure are controlled through a main air release valve and a gate finger. The set value calculation model is formed by a one-dimensional variable cross-section tube unsteady Euler equation set, and a main injection pressure set value and a static pressure set value of a wind tunnel model are solved through computational fluid dynamics software. The main injection controller is formed by using a segmented incremental PID control algorithm, and main injection pressure at an outlet of a main ejector is regulated. The flow field controller is formed by taking a model attitude feed-forward dynamic matrix control method as a core, the total pressure of a stable section and the static pressure of a test section are regulated. The control method is good in real-time performance and high in control precision, and variations of the Mach number in a test stage are controlled to a range of 0,001.

Description

technical field [0001] The invention relates to a high-precision control structure and method for a flow field of a temporary ejection type transonic wind tunnel, and the control precision of the Mach number of the flow field can reach 0.001. Background technique [0002] A wind tunnel is a tubular test device that produces a controllable and uniform airflow. It is an important ground simulation platform for studying the law of air flow, the aerodynamic characteristics of aerospace vehicles and other objects. Wind tunnel test is the main means of obtaining aircraft aerodynamic data, evaluating and analyzing layout design and predicting flight performance. Quality and level of development. [0003] As the main platform for aerodynamic tests, the impulsive jet transonic wind tunnel needs to solve the problems of high-precision flow field control and energy consumption reduction. The development of large aircraft (my country's C919 large passenger aircraft, ARJ aircraft, etc....

AI Technical Summary

Problems solved by technology

③ Time lag. The main structure of the 2.4-meter wind tunnel is a ring-shaped pipe with a total length of nearly 200 meters. There is a certain distance between the control variable and the controlled variable in the actual physical position, which causes the change of the control variable to not directly affect the controlled variable. , for example, the distance between the main exhaust valve and the stable section is nearly 60 meters, so that there is a lag in the effect of the main exhaust valve on the total pressure

However, since the Mach number cannot be directly measured, according to the subsonic one-dimensional isentropic flow theory, the Mach number is calculated from the total pressure and the static pressure via the formula, but this relationship is nonlinear, which is not conducive to the precise control of the flow field

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