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Flow field precise control system for DC transient impact type transonic wind tunnel and control method

A precise control, transonic technology, applied in the field of wind tunnel testing, can solve the problems of inaccurate resistance measurement accuracy, difficulty in accurately obtaining the resistance increment of external objects, difficulty in meeting the design requirements of aircraft, etc., and achieve the effect of improving test efficiency

Pending Publication Date: 2020-01-17
AVIC SHENYANG AERODYNAMICS RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Aircraft whose aerodynamic characteristics are very sensitive to changes in Mach number, the drag measurement accuracy is not accurate enough by using the conventional Mach number control method
Such resistance measurement accuracy is difficult to accurately obtain the resistance increment of external objects
It can be seen that when the conventional Mach number control method is adopted, it is difficult to meet the design requirements of the aircraft, and it is necessary to carry out research on the precise control technology of the flow field Mach number for the direct current impulse wind tunnel

Method used

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  • Flow field precise control system for DC transient impact type transonic wind tunnel and control method
  • Flow field precise control system for DC transient impact type transonic wind tunnel and control method
  • Flow field precise control system for DC transient impact type transonic wind tunnel and control method

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Experimental program
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Effect test

specific Embodiment approach 1

[0056] A flow field precise control system of a DC impulsive transonic wind tunnel, such as figure 1 As shown, it includes control center computer, tapping foot control computer, grid finger controller, flow field controller, grid finger drive equipment and pressure regulating valve electro-hydraulic system; the control center computer is bidirectionally connected to the grid finger controller through Ethernet , the grid finger controller is bidirectionally connected to the grid finger drive equipment, the tapping foot control computer is bidirectionally connected to the flow field controller through Ethernet, and the flow field controller is bidirectionally connected to the electro-hydraulic system of the pressure regulating valve;

[0057] Working process: The control center computer is connected to the grid finger controller through the industrial Ethernet of the test site to realize the control of the grid finger drive equipment, and at the same time control the electro-hyd...

specific Embodiment approach 2

[0064] A control method implemented on the flow field precise control system of a direct current impulse transonic wind tunnel based on the specific implementation mode 1, such as Figure 4 shown, including the following steps:

[0065] Step 1, start, first determine whether the reading of the line sensor is normal, if it is abnormal, it will alarm and end, otherwise continue to step 2;

[0066] Step 2. Before blowing, adjust each node of the super-expansion section of the wind tunnel to a given initial size, and then move the grid finger section to the preset position;

[0067] Step 3. Open the pressure regulating valve to control the total pressure in the stable section to ensure that the total pressure in the stable section is stable within the error band;

[0068] Step 4. After the total pressure is stabilized, use the gate finger controller to control the gate finger drive equipment to perform Mach number control, so that the Mach number remains within the error band;

...

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Abstract

The invention discloses a flow field precise control system for a DC transient impact type transonic wind tunnel and a control method, which belong to the technical field of wind tunnel tests, and aimat the problem that existing equipment fails and cannot be braked in time. The flow field precise control system comprises a control center computer, an attack angle control computer, a gate finger controller, a flow field controller, gate finger driving equipment and a pressure regulating valve electro-hydraulic system, wherein the gate finger driving equipment comprises a gate finger device, the grid finger device comprises two groups of gate finger sections arranged at upper and lower wall plates of a second throat of a wind tunnel super-expansion section, each group of gate finger sections comprises six wing-shaped gate finger pieces, each group of gate finger sections are respectively fixed on upper and lower gate finger trolleys, each gate finger trolley is provided with four columns of linear guide rails, and a servo electric cylinder is provided with a linear displacement sensor. Therefore, the purpose of precisely controlling a Mach number of the flow field of the DC transient impact type transonic wind tunnel is achieved; and the control method solves the problem of Mach number control precision within a range that M is greater than or equal to 1.0 and less than or equalto 1.2 by adopting a control mode integrating PID control and feedforward control for the gate fingers and performing optimized control over the flow field.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel tests, and in particular relates to a flow field precise control system and a control method of a DC impulse type transonic wind tunnel. Background technique [0002] With the development of the aerospace industry, aircraft design has higher and higher requirements for the accuracy of wind tunnel test data, especially the aircraft aerodynamic shape optimization test and the accurate measurement test of external storage resistance. At the same time, due to the aircraft aerodynamic shape The more complex the wind tunnel test data is, the more sensitive it is to the influence of the Mach number control accuracy of the flow field. Therefore, the requirements for the Mach number control accuracy of the wind tunnel are getting higher and higher. [0003] The research shows that the error of the model's aerodynamic coefficient decreases with the increase of the Mach number when the errors of the bala...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/04
CPCG01M9/04
Inventor 张军强易家宁刘广宇鲁文博王争取刘斌马莹高琦
Owner AVIC SHENYANG AERODYNAMICS RES INST
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