Layering temperature and ablation amount synchronous measurement method and device, and application

Abstract

The invention discloses a layering temperature and ablation amount synchronous measurement method and device, and an application, and relates to the technical field of measurement. The invention provides a layering temperature and ablation amount synchronous measurement device which comprises a base body, the base body is installed in an opening formed in a heat-proof layer, the outer surface of the top of the base body is flush with the outer surface of the top of the heat-proof layer, the base body is made of a material with the same or similar thermal diffusion coefficient and ablation resistance as the heat-proof layer, temperature-sensitive elements are arranged at different height positions of the base body, the temperature-sensitive elements are connected with wires, the wires are connected with an external measuring circuit, and the surfaces of the temperature-sensitive elements and the surfaces of the wires are coated with high-temperature-resistant insulating materials used for high-temperature-resistant insulating treatment. According to the invention, the base body and the heat-proof layer have the same heat conduction capability and ablation speed, high-precision synchronous measurement of the ablation amount can be realized, ablation amount measurement and layering temperature measurement are integrated, and errors caused by measurement of the ablation amount and the layering temperature in two times by a measurement device are avoided.

Description

technical field [0001] The invention relates to the field of measurement technology, in particular to a method, device and application for synchronous measurement of layered temperature and ablation amount. Background technique [0002] When the spacecraft re-enters the atmosphere, the outer surface of the structure is exposed to the high-temperature environment brought by high-speed flight, and the maximum temperature can exceed 2000°C. Generally, metal structures cannot withstand this high temperature. Therefore, it is generally necessary to cover the outside of the metal structure with a high-temperature-resistant composite material structure. , called the heat shield. Under the action of high temperature, the outer surface of the heat protection layer will burn, and the combustion will take away the surface material, so that the surface of the heat protection layer will retreat, which is called the surface ablation retreat. [0003] As the spacecraft flies in the atmosp...

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Problems solved by technology

However, due to the large interface thermal resistance between the thermocouple and the hole wall of the heat-proof layer, the measurement results have large errors, and are limited by the deep hole processing capability and the size of the thermocouple. Generally, the distance between layers is large and the integration is poor. At the same time, the data of the high temperature gradient area on the surface cannot be obtained.

[0005] In addition, since the measurement of delamination temperature and ablation amount belong to two measurement technologies, simultaneous measurement cannot be realized at present, which will bring more errors to the heat protection design, which is not conducive to improving the design accuracy

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