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Method for measuring surface heat flow of embedded thermocouple

A measurement method and thermocouple technology, which are applied to measurement devices, heat measurement, thermometers using electrical/magnetic components directly sensitive to heat, etc., can solve the problems of persecuting the structure of aircraft, affecting heat flow measurement, etc., and reducing calculation steps. , the effect of high calculation accuracy and simple structure

Active Publication Date: 2018-07-17
CHINA ACAD OF AEROSPACE AERODYNAMICS
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AI Technical Summary

Problems solved by technology

[0005] The technical problem solved by the present invention is: in view of the problems in the prior art of measuring aircraft model material that the heat flow is easy to persecute the aircraft display structure and affect the heat flow measurement of the material display, a method for measuring the heat flow on the surface of the embedded thermocouple is proposed. Arrange thermocouple sensors on the inner surface of the model to measure and calculate the heat flow value on the model surface

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  • Method for measuring surface heat flow of embedded thermocouple
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  • Method for measuring surface heat flow of embedded thermocouple

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Embodiment Construction

[0038] The method for measuring heat flow on the surface of a built-in thermocouple provided by the present invention does not need to destroy the surface structure of the aircraft, and only requires the thermal and physical parameters of the material to be stable. Measurement of surface heat flow. This method arranges multiple thermocouple sensors on the inner surface of the model to measure and obtain the temperature of the internal measuring point and the higher order derivative of the temperature change with time, and obtain the heat flow on the surface of the model by reverse calculation through the local temperature and heat flow data of the embedded measuring point value.

[0039] The present invention is achieved through the following technical solutions.

[0040] The method for measuring heat flow on the surface of the embedded thermocouple of the present invention includes a method for manufacturing and installing the thermocouple, a method for measuring high-order ...

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Abstract

A method for measuring the surface heat flow of an embedded thermocouple is provided. The thermocouple is installed on the inner surface of the model material of an aircraft by punching the inner surface, thereby ensuring the integrity of the surface of the model. A relationship between temperature and time is obtained according to a relationship between temperature and thermoelectric potential and a relationship between the thermoelectric potential and time without affecting the measurement accuracy. In a calculation process, the differentiator of an acquisition system is configured to visually reflect a derivative relationship to ensure the accuracy of the calculation. Further, according to the obtained derivative relationship, and the parameters of the thermocouple and the aircraft model material, the calculation of the surface heat flow value is completed. The method is high in measurement accuracy, good in stability, and easy to operate.

Description

technical field [0001] The invention relates to a method for measuring heat flow on the surface of a built-in thermocouple, which belongs to the field of aerodynamic thermal tests of high-speed aircraft. Background technique [0002] When a hypersonic vehicle flies at a high Mach number, there will be a very serious "thermal barrier" problem. Therefore, the surface thermal protection of a hypersonic vehicle is directly related to the flight safety of a hypersonic vehicle. In the actual development of a hypersonic vehicle, its The measurement method of surface temperature and heat flow has always been one of the key issues restricting the development of hypersonic vehicles. The surface thermal environment of a hypersonic vehicle is characterized by high Mach number, high temperature and high heat flux, especially for a re-entry hypersonic vehicle, the surface heat flux often reaches MW / m within a few minutes of its re-entry process 2 The stagnation point temperature will app...

Claims

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Application Information

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IPC IPC(8): G01K17/00G01K7/02
CPCG01K7/02G01K17/00
Inventor 马元宏赵学军向星居
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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