Solid rocket engine combustion chamber shell forming method

Abstract

The invention relates to a solid rocket engine combustion chamber shell forming method which comprises the following steps: firstly, providing a mandrel and an assembled shell, and sleeving sealing rings at two ends of the mandrel; forming a heat insulation air bag on the surface of the assembled shell; connecting a pressure measuring device, an inflating device and a pressure stabilizing device to the sealing rings at the two ends of the heat insulation air bag; after the heat-insulating air bag is inflated to specified air pressure, starting a pressure stabilizing device, winding fibers on the surface of the heat-insulating air bag, performing high-temperature curing, and integrally curing the heat-insulating air bag and the fiber layer into a solid rocket engine combustion chamber shell; and finally, removing the mandrel and the assembled shell. The heat insulation air bag is used as the winding core mold for fiber winding, the winding core mold is used as the heat insulation structure of the combustion chamber shell after the fiber layer is cured, so that separation is not needed; the winding core mold and the fiber layer form the combustion chamber shell together, and the core mold cost is saved. The heat insulation air bag can keep stable air pressure in the winding forming and high-temperature curing process, and the problem that the appearance structure of a core mold deviates from the design requirements due to thermal expansion is avoided.

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.

Images