Forming method and tool for composite material C-shaped beam

A technology of composite materials and molding methods, which can be applied to other household appliances, household appliances, household components, etc., can solve the problems of unfavorable manufacturing efficiency and manufacturing accuracy, the impact of C-beam molding quality, easy to produce wrinkles, and bending, etc., to achieve Improve the curing effect, simplify the molding difficulty, and improve the molding quality

Active Publication Date: 2020-05-01
COMAC +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, when the C-type blank is transferred to the curing tooling, it needs to be repositioned, and the operation is complicated, which is not conducive to improving manufacturing efficiency and manufacturing accuracy. In the transfer process, the C-type blank is prone to wrinkles and folds due to its thin wall thickness. Defects such as bending will have a great impact on the final forming quality of the C-beam

Method used

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  • Forming method and tool for composite material C-shaped beam
  • Forming method and tool for composite material C-shaped beam
  • Forming method and tool for composite material C-shaped beam

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Embodiment Construction

[0038] The technical solutions of the present invention will be further described below in conjunction with the accompanying drawings and through specific implementation methods.

[0039] This embodiment provides a method for forming a composite C-beam. By using this forming method, the composite material plate 1 can be made into a C-beam required on aircraft and other equipment. The C-beam has a "C"-shaped structure as a whole. It includes a top plate and two side plates protruding from both ends of the top plate. Specifically, such as figure 1 As shown, the molding method specifically includes the following steps:

[0040] S1. Positioning the composite material plate 1 on the forming surface of the preforming tooling 2, performing thermal diaphragm preforming on the composite material plate 1 to form a C-shaped blank;

[0041] S2. Remove the cover plate 3 at the end of the preforming tooling 2, so that the internal cavity 201 of the preforming tooling 2 communicates with t...

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Abstract

The invention discloses a forming method and tool for a composite material C-shaped beam, and belongs to the technical field of composite material forming. The forming method comprises the steps of 1,positioning a composite material plate on a forming surface of a preforming tool, and performing thermal diaphragm preforming on the composite material plate to form a C-shaped material sheet; 2, removing a cover plate at the end part of the preforming tool to enable an inner cavity of the preforming tool to communicate with the outside; 3, fixing the preforming tool on a base of a curing tool; and 4, curing and molding the C-shaped material sheet to form the C-shaped beam. According to the forming method, the preforming tool and the C-shaped material sheet are integrally moved, so that the secondary positioning is avoided, the manufacturing is simplified, the phenomena of folds, bending and the like caused by the separate movement of the C-shaped material sheet are avoided, and the forming quality of the C-shaped beam is improved.

Description

technical field [0001] The invention relates to the technical field of composite material forming, in particular to a forming method and forming tooling of a composite material C-shaped beam. Background technique [0002] Composite materials are materials with new properties composed of two or more materials with different properties through physical or chemical methods. With the rapid development of composite material manufacturing technology, composite materials have been widely used in the field of civil aviation. The three main structural parts of the aircraft, including wall panels, long trusses and beams, can all be made of composite materials. [0003] The C-beam made of composite material is an important structural part on the aircraft. In the prior art, the thermal diaphragm process is generally used to manufacture the C-beam. The traditional thermal diaphragm process includes two processes of preforming and forming. Each process has a corresponding tooling. After ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/38B29C70/34B29L31/30
CPCB29C70/342B29C70/38B29L2031/3076
Inventor 沈卫国刘卫平陈菲晏冬秀孙凯赵科新肖清明余永波赵强徐鹏
Owner COMAC
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