Aircraft component strength test heating device and method thereof

Abstract

The application belongs to the technical field of aircraft component strength testing, and in particular relates to a heating device for testing the strength of aircraft components, including: a box body, which has an inert gas inlet communicating with its internal space, an inert gas outlet communicating with its internal space, and a The radiation heating window connected in space; the graphite heating element, the graphite heating element is set in the inner space of the box; the glass, the glass is set in the radiation heating window, and the radiation heating window is blocked; the graphite heating element can pass through the glass to heat the aircraft parts Radiant heating. In addition, it relates to a heating method for the strength test of aircraft components implemented based on the above-mentioned heating device for strength test of aircraft components.

Description

technical field [0001] The application belongs to the technical field of strength testing of aircraft components, and in particular relates to a heating device for strength testing of aircraft components and a method thereof. Background technique [0002] When the aircraft is flying at high speed, the surface is subjected to a large aerodynamic thermal load. When performing strength tests on relevant aircraft components, it needs to be heated to simulate the environment in which the aircraft is flying at high speed. [0003] In some aircraft component strength tests, graphite heating elements are designed for radiation heating. In order to avoid oxidation failure of graphite heating elements at high temperatures, current graphite heating element radiation heaters are mostly set in vacuum tanks when working. This technical solution There are the following defects: [0004] 1) It is difficult to ensure effective vacuum in the vacuum tank, the reliability is poor, and the oper...

AI Technical Summary

Problems solved by technology

[0004] 1) It is difficult to ensure effective vacuum in the vacuum tank, the reliability is poor, and the operating cost is high;

[0005] 2) Low pressure in the vacuum tank, in this environment, the graphite heating element is prone to discharge;

[0006] 3) The heated aircraft parts also need to be placed in the vacuum tank at the same time, and the size of the heated aircraft parts is limited by the size of the vacuum tank

[0007] The above-mentioned defects of the existing scheme make it difficult to realize the effective simulation of the high-temperature environment of the aircraft components when the aircraft is flying at high speed during the strength test of the aircraft components, and cannot obtain accurate test data, and cannot contribute to the design and improvement of aircraft components. Provide effective data support

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