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Large-opening composite shell, forming method and forming tool

A technology of composite materials and molding methods, applied in jet propulsion devices, rocket engine devices, machines/engines, etc., to achieve the effects of reducing the difficulty of molding process, simplifying the structure, and improving the molding process

Pending Publication Date: 2021-04-13
内蒙动力机械研究所 +1
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  • Description
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  • Application Information

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Problems solved by technology

[0005] The technical problem to be solved by the present invention is to provide a composite material shell with a large opening to solve the problem of rapid prototyping composite material shells

Method used

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  • Large-opening composite shell, forming method and forming tool
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  • Large-opening composite shell, forming method and forming tool

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Embodiment Construction

[0029] The present invention will be further described below in conjunction with the accompanying drawings and with the specific embodiment of the removal operation of a certain type of solid rocket motor nozzle blockage.

[0030] 1. Large opening composite material shell structure

[0031] as attached figure 1 As shown, it is a schematic diagram of a light-weight, high-pressure and powerful open composite material shell, with front joints 1 and rear joints 4 at both ends, the inner layer is a heat insulating layer 2, and the outer layer is a fiber-reinforced plastic shell 3. The outer layer is a carbon fiber / epoxy composite layer.

[0032] According to the structural size and performance requirements of the solid rocket motor combustion chamber shell, the metal joints, heat insulation layer, composite material layer and other parameters of the large-opening composite shell are designed, and the structural scheme of the large-opening composite shell is determined. The shape ...

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Abstract

The invention relates to a large-opening composite material shell, a forming method and a forming tool. The large-opening composite material shell comprises a front joint, a fiber reinforced plastic shell and a rear joint, the appearances of the connecting parts of the front joint and the fiber reinforced plastic shell and the connecting parts of the rear joint and the fiber reinforced plastic shell are of inverted cone structures, and the inverted cone angle ranges from 0.3-1 degree; a forming process is divided into the procedures of heat insulation layer coating, core mold combination, laying and winding and curing; the forming tool comprises a main shaft, a front connector positioning disc, a winding integral metal core die and a rear connector positioning disc. The structure is simplified, longitudinal reinforcing fibers adopt unidirectional fiber cloth layers and circumferential reinforcing fibers adopt a circumferential winding forming method, so that the winding difficulty is reduced, and the production efficiency is improved; the light weight and high pressure performance of the large-opening composite material shell are ensured, good manufacturability is achieved, and the requirement for efficient batch production is met.

Description

technical field [0001] The invention relates to a composite material shell, in particular to a composite material shell with a large opening, a molding method and a molding tool. Background technique [0002] Lightweight, high-pressure and high-strength composite shells are key components to promote the upgrading of solid rocket motor shells. Existing composite material shells are usually prepared by sand core molds or split composite core molds, and longitudinal winding + hoop winding molding methods. [0003] The traditional domestic composite material shell is mainly prepared by sand core mold wet winding molding technology. Generally, the sand core mold is used as the winding mandrel. The sand core mold preparation process has a long cycle and cannot be reused. The composite shell with head structure is prepared by longitudinal winding + hoop winding molding method, such as patent CN 107901468 A. The split and separable cylinder is used as the winding mandrel, which so...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/30F02K9/34
CPCB29C70/30F02K9/34
Inventor 王永迪王峰郭若李恒杜成宁
Owner 内蒙动力机械研究所
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