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A composite measurement device and method for interlayer temperature and carbonization degree of heat-proof layer

A technology of carbonization degree and measuring device, which is applied in the field of measurement, can solve the problems of not being able to measure interlayer temperature and pyrolysis carbonization degree at the same time, achieve the effect of saving quantity, solving inconsistent carbonization degree, and improving the degree of analysis

Active Publication Date: 2019-03-26
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST +1
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Problems solved by technology

[0004] The technical solution of the present invention is to overcome the deficiencies of the prior art and provide a composite measuring device and method for interlayer temperature and carbonization degree of the heat-proof layer, aiming at overcoming the problem of not being able to measure the interlayer temperature and pyrolysis carbonization degree at the same position at the same time problem, improving the accuracy of the acquired measurement data, and, the analyzability of the measurement data

Method used

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  • A composite measurement device and method for interlayer temperature and carbonization degree of heat-proof layer
  • A composite measurement device and method for interlayer temperature and carbonization degree of heat-proof layer
  • A composite measurement device and method for interlayer temperature and carbonization degree of heat-proof layer

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Embodiment Construction

[0048] In order to make the purpose, technical solution and advantages of the present invention clearer, the following will further describe the public implementation manners of the present invention in detail with reference to the accompanying drawings.

[0049] refer to figure 1, which shows a schematic structural diagram of a composite measuring device for interlayer temperature and carbonization degree of a heat-proof layer in an embodiment of the present invention. In this embodiment, the composite measuring device for interlayer temperature and carbonization degree of the heat-proof layer includes: a mandrel assembly 1 and a base 2 of hollow structure, and the mandrel assembly 1 is installed on the base 2 . Wherein, the mandrel assembly 1 includes: an upper mandrel 11 , a lower mandrel 12 , a primary winding protection layer 13 , a secondary winding protection layer 14 , an alloy wire 15 and at least one thermocouple.

[0050] Such as figure 1 As shown, in this embodim...

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Abstract

The invention discloses a composite measuring device and method for interlayer temperature and carbonization degree of a heat-proof layer, wherein the method comprises: a mandrel assembly and a base with a hollow structure, and the mandrel assembly is installed on the base; the mandrel assembly includes: Mandrel, lower mandrel, primary winding protective layer, secondary winding protective layer, alloy wire and at least one thermocouple; upper mandrel and lower mandrel are connected; primary winding protective layer is wrapped around the upper mandrel and lower mandrel The surface; the secondary winding protective layer is wrapped on the outer surface of the primary winding protective layer; the alloy wire is arranged between the primary winding protective layer and the outer surfaces of the upper mandrel and the lower mandrel, and the secondary winding protective layer and the primary winding protection Between the layers; at least one thermocouple is embedded in the upper mandrel and the lower mandrel respectively. The invention overcomes the problem that the interlayer temperature and the degree of pyrolysis carbonization at the same position cannot be measured at the same time, and improves the accuracy of the acquired measurement data and the analyzability of the measurement data.

Description

technical field [0001] The technical field of measurement of the present invention relates in particular to a composite measurement device and method for interlayer temperature and carbonization degree of a heat-proof layer. Background technique [0002] When a near-space vehicle flies at hypersonic speed, aerodynamic heating will cause the temperature of the heat shield to rise and generate a temperature gradient. For the heat-resistant layer of resin-based materials that are widely used, long-term flight will cause serious ablation, pyrolysis and carbonization. The measurement of the interlayer temperature of the heat-resistant layer in the flight test is helpful to understand the flight thermal environment It can be used to judge the severity of the ablation; the measurement of the degree of pyrolytic carbonization of the heat-resistant layer is helpful to judge the state of the heat-resistant layer. Based on the measurement data of the interlayer temperature and the deg...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01K7/02G01N27/04
CPCG01K7/02G01N27/041
Inventor 陈伟华季妮芝杨红亮刘泉高扬王振峰周启超颜维旭刘波王少慧
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST
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