Ultrahigh-temperature gradient heat insulation material and preparation method thereof

Abstract

The invention discloses an ultrahigh-temperature gradient heat insulation material and a preparation method thereof. The ultrahigh-temperature gradient heat insulation material comprises an ultrahigh-temperature heat insulation material layer which is positioned at one high-temperature side, a phase-change heat absorbing insulation material layer positioned at the outer side of the ultrahigh-temperature heat insulation material layer, a medium-temperature heat insulation layer positioned at the outer side of the phase-change heat absorbing insulation material layer, a low-temperature heat insulation layer positioned at the outer side of the medium-temperature heat insulation layer, and radiating shielding layers which are respectively arranged between two adjacent layers of the ultrahigh-temperature heat insulation material layer, the phase-change heat absorbing insulation material layer, the medium-temperature heat insulation layer and the low-temperature heat insulation layer and positioned at the outer side of the low-temperature heat insulation layer; the radiating shielding layers are used for resisting radiation; the layers are integrally combined. The ultrahigh-temperature gradient heat insulation material has the characteristics of being resistant to ultrahigh temperature and long in service life.

Description

technical field [0001] The invention relates to the technical field of thermal insulation materials, in particular to an ultra-high temperature gradient thermal insulation material and a preparation method thereof. Background technique [0002] With the rapid development of aerospace technology, thermal protection systems and materials have become one of the most important key technologies that restrict the success of aircraft research and development. With the continuous improvement of the flight Mach number, the requirements for the temperature of the thermal protection material are getting higher and higher. During operation, the temperature of the outer wall of the combustion chamber is as high as 2000K or more. In order to protect the metal shell of the engine and its surrounding electronic equipment, reduce Heat dissipation and the obvious infrared signal characteristics brought by it, the outer wall of the combustion chamber is protected by ultra-high temperature heat...

AI Technical Summary

Problems solved by technology

[0004] With the development of aerospace technology, thermal protection materials with higher temperature resistance are gradually developed, among which ZrC / aerogel and resin polymer laminated composite materials have higher temperature resistance, but the material has long-term heat insulation performance downside downside

There are also zirconia materials, but this material has the disadvantage of serious radiation heat transfer at high temperatures

[0005] It can be seen that the existing thermal protection materials have low temperature resistance, about 1800-2000K, and the use time is short, about tens of seconds to 400 seconds, which can no longer meet the high Mach number and long-term flight needs of high-speed aircraft.

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