Automatic blade-coating method for solid propellant cladding lining layer of rocket engine

Abstract

The invention discloses an automatic blade coating method for a solid propellant cladding lining layer of a rocket engine. The automatic blade-coating method comprises the steps of preparation beforecoating, distributing of material slurry, blade coating of the material slurry and beforehand solidification; during distributing of the material slurry, the quantitative material slurry of the cladding lining layer is distributed on a cladding face, and the material slurry is distributed in a strip shape; and during blade coating of the material slurry, an automatic blade-coating program is started, even blade coating is achieved by constant-speed moving of a brush blade on the cladding face. During mechanical blade coating, the rotating speed of a blade-coating piece, the displacement speedand the displacement amount of a brush rod in the radial and axial directions are controlled through a program by utilizing a numerical control machine tool, and even coating and adjusting and controlling of the blade-coating speed are achieved; and the brush blade on the rigid brush rod is made of ox-tendon imitating plate composite materials with the certain strength and toughness, the brush rodand the brush blade are firmly positioned, so that angle offset is not generated between the brush rod and the brush blade. The automatic blade coating method for the solid propellant cladding lininglayer of the rocket engine can be widely applied to automatic blade coating of the cladding lining layer between solid rocket engine heat insulation materials and a solid propellant and has the advantages that the structure is simple, the process is controllable, the quality is reliable, and safety and effectivity are achieved.

Description

technical field [0001] The invention relates to a coating transition layer scraping coating process method between a solid rocket motor heat insulating material and a solid propellant, in particular to an automatic scraping coating method for a solid propellant coating lining layer of a rocket motor. Background technique [0002] The solid propellant coated liner is an important part of the solid rocket motor combustor. The combustion chamber of a solid rocket motor is usually composed of a shell, a thermal insulation layer, a cladding liner, and a solid propellant. The cladding liner is a viscoelastic buffer transition layer that firmly bonds the thermal insulation layer and the solid propellant. Structural performance and coating process directly affect the performance of solid rocket motors. Traditional lining coating methods are mainly manual brushing, spray coating, rolling coating, high-speed centrifugal dispersion coating, etc. Their common shortcomings are: difficul...

AI Technical Summary

Problems solved by technology

Traditional lining coating methods are mainly manual brushing, spray coating, rolling coating, high-speed centrifugal dispersion coating, etc. Their common shortcomings are: difficult to guarantee quality, subject to human factors, high safety risks, and hidden dangers of accidents Large, uneven lining thickness, low production efficiency