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Ejector-driven closed-loop recirculation temporary impulse supersonic wind tunnel flow field control method

A control method and closed-loop control technology, applied in the direction of electric fluid pressure control, fluid pressure control, non-electric variable control, etc., can solve the problem that the temporary supersonic wind tunnel cannot establish a stable supersonic flow field, etc.

Active Publication Date: 2018-08-10
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology

[0005] The object of the present invention is to provide a temporary supersonic wind tunnel with closed-loop backflow driven by ejection, aiming at the problem that a stable supersonic flow field with different M numbers cannot be established under the same total pressure in the closed-loop backflow temporary supersonic wind tunnel. Cave Flow Field Control Method

Method used

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  • Ejector-driven closed-loop recirculation temporary impulse supersonic wind tunnel flow field control method

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[0064] The present invention will be further described in detail below in conjunction with the accompanying drawings, so that those skilled in the art can implement it with reference to the description.

[0065] It should be understood that terms such as "having", "comprising" and "including" as used herein do not entail the presence or addition of one or more other elements or combinations thereof.

[0066] figure 1 It is a schematic diagram of the aerodynamic profile of the wind tunnel related to the present invention, such as figure 1 As shown, the wind tunnel includes: return pipeline; fourth corner section 1, stable section 2, contraction section 3, nozzle section 4, test section 5, bracket section 6, diffuser section 7, injection 8, the first corner section 9, the second corner section 10, the auxiliary air intake system 11, the backflow regulating valve 12, the fifth corner section 13, the exhaust system 14 and the third corner section 15;

[0067] Wherein, the ejecto...

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Abstract

The invention discloses an ejector-driven closed-loop recirculation temporary impulse supersonic wind tunnel flow field control method. An ejector arranged behind a diffusion section is adopted as themain drive of a wind tunnel flow field, under the cooperation of a recirculation regulating valve, an assisting air admission pressure regulating valve and an exhaust throttle valve, a stable supersonic flow field is established, wherein precise control of the total pressure of a stabilizing section is achieved under the mutual action of a pressure regulating valve of the ejector and the assisting air admission pressure regulating valve, and on the basis of the precise control of the total pressure, the establishing of stable supersonic flow fields with different M values under the same operation total pressure in a temporary impulse supersonic wind tunnel can be achieved under the cooperation of a nozzle profile surface and a diffusion section profile surface. By means of the method, thesimulation of negative pressure working conditions can be achieved in a closed-loop recirculation temporary impulse supersonic wind tunnel, the operating envelope and simulation range of the wind tunnel are effectively expanded, and the total pressure of a stabilizing section needed by the establishing of a supersonic flow field when the M value of a traditional temporary impulse wind tunnel is high can be significantly reduced, which facilitates the aerodynamic loading of a model and the improvement of the measuring accuracy of a strain gauge balance of the wind tunnel.

Description

technical field [0001] The invention relates to the field of flow field control of a temporary supersonic wind tunnel, in particular to a method for controlling the flow field of a semi-return temporary supersonic wind tunnel for an ejector system and an exhaust throttling system. Background technique [0002] A wind tunnel is a pipeline-shaped ground test simulation device that can artificially generate and control airflow to simulate the flow of air around an aircraft or object, measure the effect of airflow on an object, and observe physical phenomena. According to the simulation speed, wind tunnels are divided into low-speed wind tunnels (M≤0.4), high-speed wind tunnels (0.4<M≤4.5) and hypersonic wind tunnels (M≥5.0). In the high-speed wind tunnel, it is divided into sub-transonic wind tunnel (M=0.4~1.4) and supersonic wind tunnel (M=1.5~4.5). The wind tunnel simulates the corresponding M number by controlling the pressure ratio of the airflow in the wind tunnel duct...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D16/20G01M9/04
CPCG01M9/04G05D16/2026
Inventor 熊波徐来武阎成陈海峰秦建华丁寿和顾海涛庞旭东蒋明华杨轶成祖孝勇唐亮
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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