Ablation-proof structure of solid rocket engine

Abstract

Disclosed is an ablation-proof structure of a solid rocket engine. The ablation-proof structure of the solid rocket engine comprises a pressure-bearing structure casing, a thermal insulating layer and an anti-scouring low-residue protective layer, wherein the thermal insulating layer is located in the pressure-bearing structure casing, and the anti-scouring low-residue protective layer is embedded into the inner surface of the thermal insulating layer. By means of the technical scheme, solid residues generated during ablation of the thermal insulating layer can be reduced, and moving parts are prevented from being blocked.

Description

technical field [0001] The invention relates to the technical field of solid rocket motors, in particular to an anti-ablation structure for solid rocket motors. Background technique [0002] The kinetic energy that the solid rocket motor relies on comes from the gas generated by the high-pressure combustion reaction of the solid propellant packed in the motor casing. The gas expands in the nozzle and accelerates to a very high speed, so that the energy in the gas is converted into the kinetic energy of the exhaust gas. During the combustion process of the propellant, the thermal insulation layer of the engine will be ablated after being scoured by high-temperature gas. The ablation process of the insulation layer will produce solid residues and fall off. These solid residues flow together with the high-temperature gas. Some of the solid residues will flow out through the nozzle, and some will adhere to other parts of the engine. If these solid residues are attached to the ...

AI Technical Summary

Problems solved by technology

Once the operation of the moving parts is restricted or stuck, it will bring incalculable accidents

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