Frosting experiment device and application
A kind of experimental device and frosting technology, which is applied in the direction of measuring device, aerodynamic test, machine/structural component test, etc., can solve the problem that the frost layer cannot directly observe the surface flow field characteristics of the frost layer at supersonic speed, etc.
Pending Publication Date: 2022-07-12
XI AN JIAOTONG UNIV
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[0005] Based on the problem that the existing measuring device cannot directly observe the surface flow field characteristics of the frost layer at supersonic speed and the impact of the shock wave on the frost layer, this application provides a frosting experimental device and its application
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[0025] Hereinafter, specific embodiments of the present application will be described in detail with reference to the accompanying drawings, from which those skilled in the art can clearly understand the present application and be able to implement the present application. Without departing from the principles of the present application, the features of the various embodiments may be combined to obtain new embodiments, or instead of certain features of certain embodiments, to obtain other preferred embodiments.
[0026] Schlieren method is a commonly used optical observation method. The basic principle is to use the refractive index gradient of light in the measured flow field to be proportional to the airflow density of the flow field for measurement. When the light passing through the measured flow field passes through the front blade of the high-speed camera, the area with high density is blocked by the knife edge due to the large deflection, and dark lines appear on the sc...
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The invention belongs to the technical field of observation equipment, and particularly relates to a frosting experiment device and application. An existing measuring device cannot directly observe the surface flow field characteristics of a frost layer under supersonic speed and the influence of shock waves on the frost layer, and there is no appropriate model for predicting the frosting amount. The invention provides a frosting experiment device which comprises a schlieren generation mechanism, a high-speed air duct and a temperature control mechanism, the schlieren generation mechanism comprises a light source assembly and a schlieren observation assembly, the light source assembly is arranged on one side of the high-speed air duct, and the schlieren observation assembly is arranged on the other side of the high-speed air duct. The temperature control mechanism is arranged in the high-speed air duct, and when high-speed airflow in the high-speed air duct passes through the temperature control mechanism, the airflow can reach a supersonic speed state at the temperature control mechanism due to the fact that the flowing sectional area changes. And the influence of the frost layer surface flow field characteristics and shock waves on the frost layer under supersonic speed can be visually and effectively observed.
Description
technical field [0001] The application belongs to the technical field of observation equipment, and in particular relates to a frosting experiment device and application. Background technique [0002] With the development of the aerospace industry, the frosting characteristics and defrosting technology of wings have been widely concerned. At present, the use of low-temperature wind tunnel technology to simulate the flight state of the aircraft to observe the frosting and defrosting characteristics of the wing is the main test method. When the aircraft is flying at supersonic speed, the disturbance cannot be transmitted to the front of the aircraft, and the gas in front is compressed to form a concentrated strong disturbance. At this time, an interface of the compression process appears, which is a shock wave. After the shock gas density will produce a larger mutation. The shock wave has a certain influence on the thermophysical properties of the gas. However, the current ...
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IPC IPC(8): G01M9/00G01M9/06B64F5/60
CPCG01M9/00G01M9/065B64F5/60Y02T90/00
Inventor 赖天伟强铭琛侯予颜少航赵琪龚建英张兴群
Owner XI AN JIAOTONG UNIV