Aerodynamic heat full-field measurement system and method based on embedded temperature-sensitive paint

Abstract

The invention belongs to the technical field of temperature-sensitive paint measurement, and discloses an aerodynamic heat full-field measurement system and method based on embedded temperature-sensitive paint in order to solve the problem that application of a temperature-sensitive paint measurement technology is seriously limited due to carbonization and falling of a temperature-sensitive paint coating caused by high total temperature of a flow field. The excitation light source is connected with the beam expander, the imaging lens and the optical filter are sequentially and additionally arranged at the front end of the camera, an illumination area of the beam expander and an imaging area of the imaging lens coincide and cover the whole measurement sensitive unit, the excitation light source irradiates the measurement sensitive unit to generate radiation light, and the radiation light is collected by the imaging lens and then received by the camera. The method is used for measuring full-field detailed aerodynamic thermal characteristics of the hypersonic aircraft in a real flight environment. The embedded temperature-sensitive paint measuring method is not limited by the shape of the model; and the temperature-sensitive paint is sprayed on the inner wall surface of the calorimetric layer and is physically isolated from the flow field, so that the surface roughness of the model is not changed, and the flow characteristic of the flow field is not influenced at all.

Description

technical field [0001] The invention belongs to the technical field of temperature-sensitive paint measurement, and in particular relates to an aerothermal full-field measurement system and method based on an embedded temperature-sensitive paint. Background technique [0002] Hypersonic air-breathing powered aircraft work with oxygen in the air without carrying an oxidant, and have the advantages of high specific impulse, simple structure, and allow horizontal take-off and landing. Compared with rocket-powered aircraft, air-breathing-powered aircraft adopts a large number of sharp leading edge structures in order to obtain better aerodynamic performance, and the fuselage, propulsion system and thermal protection system of hypersonic air-breathing-powered aircraft adopt an integrated design, and the outflow and propulsion of the aircraft There is a strong coupling effect in the internal flow of the system. These characteristics make the design of hypersonic vehicle component...

AI Technical Summary

Problems solved by technology

The results of high-temperature wind tunnel experiments such as HEG, HIEST and JF-12 at home and abroad show that the high total temperature characteristics of the flow field in the real flight environment are the main reasons for limiting the application of temperature-sensitive paints

The high total temperature of the flow field causes a high temperature rise on the surface of the model, which causes carbonization and peeling off of the temperature-sensitive paint coating

At the same time, the high total temperature flow field is often accompanied by the phenomenon of gas radiation. The gas radiation light and the temperature-sensitive paint radiation overlap in the spectrum, which cannot be eliminated by means of filters, which severely limits the application of temperature-sensitive paint measurement technology.

[0008] To sum up, the design of hypersonic vehicles greatly depends on the refined measurement results of the heat flux field, but there is still a lack of heat flux field measurement technology under the condition of high total temperature. The aerothermal full-field measurement method of paint has important practical significance

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