A kind of solid rocket motor combustor casing forming method

Abstract

The invention relates to a method for forming a solid rocket motor combustion chamber shell. First, a mandrel and an assembled shell are provided, and sealing rings are sheathed on both ends of the mandrel; then a heat-insulating airbag is formed on the surface of the assembled shell; The pressure measuring device, the inflation device and the voltage stabilization device are connected to the sealing ring; after inflating the heat insulating airbag to the specified air pressure, the voltage stabilization device is turned on, and fibers are wound on the surface of the heat insulating airbag, cured at high temperature, and the heat insulating airbag and the fiber layer are integrated into a solid rocket motor. Combustion chamber casing; finally remove mandrel and assembled casing. The invention uses the insulating airbag as the winding core mold for fiber winding. After the fiber layer is solidified, the winding core mold is used as the thermal insulation structure of the combustion chamber shell, and the combustion chamber shell is formed together with the fiber layer without the need of detachment, thereby saving the cost of the core mold. The thermal insulation airbag can keep the air pressure stable during the process of winding molding and high-temperature curing, and avoid the problem that the shape and structure of the core mold deviate from the design requirements due to thermal expansion.

Description

technical field [0001] The invention relates to the field of winding forming, in particular to a method for forming a casing of a solid rocket motor combustion chamber. Background technique [0002] The main process of forming the traditional solid rocket motor combustion chamber shell is to assemble the head and lay the heat insulation layer on the mandrel structure, then wind the fiber layer, and release the mold after high temperature curing to form the product. The mandrel structure mainly has the assembled type Mandrel, all-metal mandrel, flushable mandrel and other rigid structures. For large combustion chamber shells, the selection of conventional mandrel solutions has problems such as high manufacturing difficulty, long cycle time, high cost, and difficulty in ensuring accuracy, especially the mandrel deflection deformation and thermal expansion deformation cannot be overcome. The core mold may also be difficult to meet the development needs of large combustion cham...

AI Technical Summary

Problems solved by technology

[0004] The invention provides a solid rocket motor combustion chamber casing molding method to solve the problems of high cost, long cycle and difficulty in ensuring the accuracy of core mold molding in the related art.

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