Self-crosslinking silicon-boron-containing high polymer matrix ablation-resistant heat insulation material and preparation method

Abstract

The invention discloses a self-crosslinking silicon-boron-containing high polymer matrix ablation-resistant heat insulation material and a preparation method, and belongs to the field of high polymercomposite materials. The material comprises, by weight, 100 parts of heat-vulcanized silicone rubber, 10-30 parts of polyborosiloxane prepolymers, 10-30 parts of white carbon black, 5-10 parts of fibers, 10-20 parts of light ablation-resistant fillers, 3-5 parts of vulcanizing agents and 1-3 parts of hydroxyl silicone oil. The method includes the steps: mixing the polyborosiloxane prepolymers andthe light ablation-resistant fillers; sequentially adding all materials to a mixer and performing plasticating; vulcanizing mixed rubber materials for three times to obtain the self-crosslinking silicon-boron-containing high polymer matrix ablation-resistant heat insulation material. The material serves under the condition of oxygen enrichment and high temperature, is subjected to carbonizing andceramic reaction in a high-temperature environment, serves as a high-temperature ablation-resistant protective layer and directly bears combined action of thermochemical ablation, gas denudation and particle erosion, and the ablation-resistant heat insulation performance of the material is effectively improved.

Description

technical field

[0001] The invention relates to the field of polymer composite material preparation, in particular to a self-crosslinking silicon-boron-containing polymer-based ablation-resistant thermal insulation material and a preparation method. Background technique

[0002] With the continuous development of the international situation, modern space vehicles and long-duration flight weapons have attracted more and more attention from countries all over the world. Subsequently, higher and higher requirements have been put forward for solid rocket ramjet engines. High-energy propellants have been widely used. The strength problem has also become more prominent due to the increase in heat transfer and the thinning of the shell. The problem of high temperature resistance, erosion resistance and ablation of the heat insulation layer is one of the core issues in the thermal structure design of the aircraft.

[0003] When the solid rocket ramjet engine is working, the harsh co...

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