A solid rocket engine lining and layered molding method

By adopting the liner layer layer forming method in a solid rocket engine, reliable interface bonding between propellant/linear layer/insulating layer is achieved, and the problem of interface bonding failure in the prior art is solved, and the interface bonding strength and reliability are significantly improved.

CN115288882BActive Publication Date: 2025-03-21SHANGHAI AEROSPACE CHEM ENG INST
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Patent Information

Application Number
CN202210784937.7
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2022-06-29
Publication Date
2025-03-21
Estimated Expiration
2042-06-29

AI Technical Summary

Technical Problem

The prior art is difficult to achieve reliable interface bonding between the propellant/liner/insulating layer, resulting in abnormally enlargement of the combustion surface of the solid rocket engine, overheating, losing strength in the shell, and even burning through or explosion.

Method used

The solid rocket engine liner layer layer forming method is adopted to achieve interface bonding by uniformly coating the base slurry on the surface of the insulating layer, intermediate layer slurry on the surface dry bottom slurry, and surface layer slurry on the gelled intermediate layer surface, and finally co-curing and molding with the propellant slurry to achieve interface bonding.

Benefits of technology

It significantly improves the interface bonding strength, improves the problem of weak strength layer of near-interface propellant, and improves the reliability of interface bonding of solid rocket engine loading.

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Abstract

The invention discloses a layered forming method for a solid rocket engine lining, firstly, a bottom layer slurry is uniformly coated on the surface of an insulation layer, and the bottom layer slurry is pre-reacted to obtain a surface-dry bottom layer of the lining layer; then, an intermediate layer slurry is uniformly coated on the surface of the surface-dry bottom layer of the lining layer, and the intermediate layer slurry is pre-reacted to obtain a gelled lining intermediate layer, and in this process, the bottom layer of the lining layer will also reach a gelled state; then, after the surface layer slurry is coated on the surface of the gelled lining intermediate layer, a propellant slurry is poured; finally, the gelled lining bottom layer, the intermediate layer, and the surface layer slurry coated on the surface of the gelled lining intermediate layer are cured and formed together with the propellant slurry to complete the interface bonding. The invention can increase the interface bonding strength by more than 20%, effectively improve the problem of the weak strength layer of the propellant near the interface, and improve the reliability of the interface bonding of the solid rocket engine charge.
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