Heat insulation layer structure of solid rocket engine long-tail nozzle, and preparation method thereof

Abstract

The invention provides a heat insulation layer structure of a solid rocket engine long-tail nozzle, and a preparation method thereof. The heat insulation layer structure comprises an ablation layer, afirst heat insulation layer and a low-density heat insulation layer which are arranged in an attached mode, wherein the ablation layer takes a phenolic resin as a matrix material and takes carbon fiber as a reinforcing material, the first heat insulation layer takes a phenolic resin as a matrix material and takes high silica glass as a reinforcing material, and the low-density heat insulation layer takes a phenolic resin added with a light filler as a matrix material and takes glass fiber as a reinforcing material. According to the heat insulation layer structure, the low-density heat insulation layer is arranged on the basis of the ablation layer and the heat insulation layer, and by utilizing the characteristic of low heat conductivity of the low-density material, under the condition that the ablation resistance is not influenced, the heat insulation performance of the heat insulation layer of the long-tail nozzle is improved, ablation and heat insulation are balanced, and the heatprevention efficiency of the heat insulation layer of the long-tail nozzle is improved; and the mass ratio of the long-tail nozzle product can be increased, and the problems of low mass ratio and highthermal conductivity of a traditional structure of the long-tail nozzle are solved.

Description

technical field [0001] The invention belongs to the technical field of composite materials, and in particular relates to a heat insulating layer structure of a long tail nozzle of a solid rocket motor and a preparation method thereof. Background technique [0002] Heat protection technology is one of the key technologies of solid rocket motors. Ablation heat protection is the most commonly used heat protection technology for solid rocket motor nozzles. The most widely used thermal protection materials for solid rocket motor nozzles are resin-based ablative composites. The ablation and heat insulation materials for long-tail nozzles of domestic engines are mostly carbon cloth / phenolic, carbon fiber / phenolic, high-silica cloth / phenolic, glass cloth / phenolic, which are formed by tape winding, layering or molding. With the development of solid rocket propulsion technology and the upgrading of tactical weapons, there are new requirements for the development of engines. On the ...

AI Technical Summary

Problems solved by technology

In order to improve the erosion resistance of the ablation layer of the carbon fiber braided layer, the method of increasing the fiber volume content is often used to solve the problem. However, due to the good thermal conductivity of carbon fiber, increasing the fiber volume content will lead to a decrease in the heat insulation performance of the ablation layer. Therefore, the traditional process is used to prepare Thermal protection materials have a certain gap in terms of long-term mechanical erosion resistance and heat insulation performance, especially on the basis of balanced ablation and heat protection, and improve heat protection efficiency, which cannot meet the needs of new weapons and equipment

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