High temperature performance thermal-mechanical coupling test platform for high temperature heat seal

A high-temperature performance, thermo-mechanical coupling technology, applied in the field of test platforms, can solve the problem of not effectively testing the resilience performance, and achieve the effect of a large heating rate

Inactive Publication Date: 2019-08-06
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

At present, there is no effective test method for its rebound performance at high temperature in China.

Method used

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  • High temperature performance thermal-mechanical coupling test platform for high temperature heat seal
  • High temperature performance thermal-mechanical coupling test platform for high temperature heat seal
  • High temperature performance thermal-mechanical coupling test platform for high temperature heat seal

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Embodiment Construction

[0028] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0029] A thermal-mechanical coupling test platform for high-temperature performance of high-temperature heat seals, including a mechanical testing machine 1, a support seat 2, an electromagnetic induction coil 4, a pressure head 5, and a heating element 7; figure 1 , figure 2 , the support seat 2 is fixedly installed on the experimental pla...

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Abstract

The invention relates to a high temperature performance thermal-mechanical coupling test platform for a high temperature heat seal. The high temperature performance thermal-mechanical coupling test platform comprises a mechanical testing machine supporting base, a pressing head, an electromagnetic induction coil and a heating body, wherein the supporting base is fixedly mounted on an experimentalplatform of a mechanical testing machine, a base is fixedly connected onto the supporting base, and the heating body is mounted on the base; the electromagnetic induction coil sleeves the heating body, and both ends of the electromagnetic induction coil are connected to high-frequency induction equipment; and a pressing rod of the mechanical testing machine is fixedly connected with the pressing head. The high temperature performance thermal-mechanical coupling test platform improves the mechanical testing machine and combines the mechanical testing machine with the high-frequency induction equipment to build the test platform, adopts induction heating as a heating mode, can provide high temperature rising rate, and is applied to ultra-high temperature thermal environment simulation tests.

Description

technical field [0001] The invention relates to the technical field of test platforms, in particular to a thermal coupling test platform for high-temperature performance of high-temperature heat seals. Background technique [0002] When the hypersonic vehicle re-enters, the high-pressure hot air flow in front of the deflected aerodynamic control wing leaks into the low-pressure control wing gap, which will generate gap inflow and its aerodynamic heating. If no precautions are taken, in severe cases, the low-temperature components at the bottom of the control wing gap of the aircraft will be damaged or even fail, which will lead to the loss of control of the aircraft. Therefore, in order to prevent the inflow of high-temperature airflow, it is necessary to perform heat insulation and sealing treatment at the gap, and the sealing treatment will not affect the deflection function of the aircraft control wing during the entire safe service period of the aircraft. During the re-...

Claims

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Application Information

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IPC IPC(8): G01N3/54
CPCG01N3/54
Inventor 解维华杨帆韩硕孟松鹤易法军许承海杨强
Owner HARBIN INST OF TECH
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