A kind of ultra-high temperature heat insulation material and preparation method thereof

Abstract

The invention discloses an ultra-high-temperature heat-insulating material prepared from carbon fiber and zirconia fiber as main raw materials. A preparation method of the ultra-high-temperature heat-insulating material comprises the following steps: firstly, uniformly mixing and dispersing the chopped carbon fiber and the zirconia fiber in deionized water containing a dispersing agent; secondly, preparing a carbon fiber-zirconia fiber composite preform by a vacuum filtering moulding method; finally, preparing a carbon fiber-zirconia fiber composite material by a press drying method. The ultra-high-temperature heat-insulating material is prepared from the carbon fiber and the zirconia fiber with relatively high elastic modulus, so that the ultra-high-temperature heat-insulating material is guaranteed to have relatively high heat-insulating performance and requirements on mechanical properties can be met; and tests show that the heat-insulating material can withstand a high temperature of at least 2000 DEG C within a short time, has the thermal conductivity of less than 0.15W / m.K and the compressive strength of greater than 0.5MPa at 1000 DEG C, and is applicable to thermal protection (passive insulation) of an outer wall of a combustion chamber of a power device of a high-speed aircraft.

Description

Technical field [0001] The invention belongs to the thermal insulation material in the technical field of thermal protection, and particularly relates to an ultra-high temperature (above 2000°C) thermal insulation material and a preparation method thereof. Background technique [0002] When the hypersonic vehicle power unit is working, the temperature of the combustion chamber wall is as high as 2100~2400℃. In order to protect the power unit and its surrounding electronic equipment, while reducing the heat dissipation and the obvious infrared signal characteristics it brings, the combustion chamber wall Ultra-high temperature insulation materials must be used for thermal protection. [0003] The American HyFly project uses a 1-inch thick ZrC / aerogel and resin polymer laminated composite material to realize the thermal insulation of the outer wall of the ramjet combustion engine (Han Jicai, Hu Ping, Zhang Xinghong, Research Progress of Ultra-High Temperature Materials, Solid Rocket ...

AI Technical Summary

Problems solved by technology

However, due to the low strength of zirconia fibers, the fibers are prone to brittle fracture under stress, so there is a safety hazard in using zirconia fiberboard heat insulation materials alone for thermal protection on the outer wall of the ramjet combustion engine

The temperature resistance of carbon fiber heat insulation materials exceeds 3000°C, but the thermal conductivity is large (above 0.43W / m.K), and it cannot meet the heat insulation requirements of the combustion chamber when used alone

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