A sample ejection type supercooled droplet impact microscopic observation system

Abstract

Disclosed is a sample piece ejection type supercooled liquid drop impact microscopic observation system. The sample piece ejection type supercooled liquid drop impact microscopic observation system comprises a heat preservation box body, a small refrigeration subsystem, a liquid drop generation subsystem, a sample piece ejection subsystem, a temperature sensor and a high-speed camera image capture subsystem. The heat preservation box body provides an enclosed environment for the system; an evaporator of the small refrigeration subsystem is mounted on the inner wall of the heat preservation box body, other components are disposed outside the heat preservation box body, and then a refrigerant loop is formed by connection through copper pipes; a main body of the liquid drop generation subsystem is located outside the heat preservation box body, a guide tube and a needle head extend into the box body, and liquid drops can be continuously dripped; the sample piece ejection subsystem is mounted in the middle of the heat preservation box body; and the temperature sensor is mounted in the heat preservation box body. By means of the sample piece ejection type supercooled liquid drop impact microscopic observation system, the actual situation of an aircraft during freezing in the air is better simulated, microscopic observation of a freezing process when the supercooled liquid drops impact on the surface of a to-be-measured sample piece is achieved, and good basis is provided for representation of the anti-icing property of a coating.

Description

technical field [0001] The invention provides a sample ejection type supercooled droplet impact microcosmic observation system, which relates to the microcosmic dynamic observation technology of the shape change and icing condition when the supercooled droplet hits a specific functional surface of a sample with a certain speed. Using a new type of supercooled liquid droplet preparation, sample ejection motion and high-speed dynamic observation scheme, this observation system is built to simulate the actual motion of the aircraft relatively realistically, which is convenient for revealing the mechanism of liquid droplet freezing on the functional surface and characterizing The anti-icing performance of the functional surface belongs to the technical field of analysis and measurement control in the technical field of instruments and meters. Background technique [0002] With the emergence of many new aircraft, such as large unmanned aerial vehicles, long-range bombers, etc., t...

AI Technical Summary

Problems solved by technology

Because the speed of the aircraft passing through the cloud layer that is prone to icing is very fast, the static water droplet icing experiment of the coating has great limitations, and cannot simulate the icing situation of the coating at high speed; and the large ice The cost of each wind tunnel experiment is particularly high, and the research on coating icing is not equivalent to the study of the flow field near the aircraft. The use of wind tunnels to study aircraft aerodynamic performance can better characterize the aircraft's force and other parameters, while icing If the experiment uses droplets with a certain speed, the movement of the droplets themselves may affect the way they freeze

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