Solid rocket engine lining forming method

Abstract

The invention provides a solid rocket engine lining forming method which comprises the following steps: spraying a binder on a charge interface of a heat insulation layer for semi-curing treatment, and then carrying out lining forming construction. The method comprises the specific steps of S1, carrying out plasma treatment on the interface of the heat insulation layer of the solid rocket engine, protecting a non-spraying surface, then installing a spraying tool in the engine, and moving into a curing oven to be installed and limited; S2, diluting the binder by using ethanol, measuring the viscosity of the slurry by using a Tu-4 cup viscometer, and controlling the viscosity to be 40s / cup to 70s / cup; S3,sieving the slurry obtained in the S2, removing bubbles, spraying the slurry to the charge interface of the heat insulation layer through spraying equipment, and semi-curing the slurry for standby application; and S4, diluting a lining raw material with trichloromethane, preparing a lining slurry, spraying the lining slurry to the semi-cured interface treated in the S3, then carrying out semi-curing, and completing solid rocket engine lining forming construction. According to the forming method provided by the invention, reliable bonding of the heat insulation layer and the lining layer can be realized.

Description

technical field [0001] The invention belongs to the technical field of solid rocket motors, uses plasma treatment and chemical bonding treatment to increase the bonding strength of the lining, and in particular relates to a forming method for the lining of the solid rocket motor. Background technique [0002] The lining layer of solid rocket motor is also called cladding layer. It is a special adhesive that connects the propellant and heat insulation layer or shell material in the combustion chamber shell. Its main function is to connect the propellant, heat insulation layer or The interface of the shell material undergoes chemical reactions and physical actions to firmly bond the propellant, thermal insulation layer or shell material together to ensure the integrity of the charge structure of the solid rocket motor during the entire life cycle, and to work in solid rocket motors At the same time, it is ensured that the propellant burns according to the designed combustion s...

AI Technical Summary

Problems solved by technology

[0003] The inner heat insulation layer of solid rocket motor is a kind of ablation-resistant material used to protect the engine casing. In the production process, the airbag preloading process is often used to complete the curing and molding process of the heat insulation layer. If the solidified gas cannot be effectively discharged during the curing process, Quality defects such as pores and air bubbles will occur, and there are often burrs and oil stains on the surface. If the insulation layer is not treated, it will easily lead to debonding between the insulation layer and the lining layer. Therefore, it is important to improve the bonding strength between the insulation layer and the lining layer. Problems that need to be solved

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