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A preform transfer and layup of composite parts and method

A composite material and prefabricated technology, which is applied in the field of aircraft structure, can solve the problems of Telar film’s non-extensibility and inability to lay up prepreg materials, and achieve the effects of improved protection, smooth surface and avoiding non-adhesive

Active Publication Date: 2022-08-05
JIANGXI CHANGHE AVIATION IND
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Because the Telar film is non-extensible and non-sticky, it cannot be laid flat on the molding tooling. It is difficult to fix it on the molding tooling with auxiliary fixing methods such as pressure-sensitive tape. If it is not fixed well, it cannot be done. Prepreg layup

Method used

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  • A preform transfer and layup of composite parts and method

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Embodiment Construction

[0025] The present invention provides a preform transfer and a method for laying up composite parts, the lay-up such as figure 1 As shown, the method includes:

[0026] ① First, paste a circle of putty strips on the tooling;

[0027] ②Then lay a piece of breathable felt at the root of the R corner on both sides of the tooling; Note: The breathable felt is laid outside the part allowance line.

[0028] ③ Install 1 vacuum nozzle on each of the R corners (4 in total), and a putty strip is allowed to be wrapped around the vacuum nozzle to ensure that it is sealed with the tooling surface;

[0029] ⑤Place another layer of isolation film / Telar, make a vacuum bag, and vacuumize to ensure that the isolation film and the tooling surface fit smoothly, and no wrinkles are allowed in the profile surface.

[0030] This method is used for 1. Narrow cavity one-way belt parts negative mold forming. Because the cavity is narrow, in order to meet the thickness and surface quality of the part,...

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Abstract

The invention belongs to the field of aircraft structures, and relates to a prefabricated body transfer and lamination of composite material parts and a method thereof. The method includes: sticking a circle of putty strips on the forming tool surface of the male mold of the tool; laying a piece of breathable felt on the root of the R corner on both sides of the tool; installing a vacuum nozzle on each of the R corners on both sides of the tool; placing a layer of Isolation film or paint film, make a vacuum bag, and vacuumize to ensure that the isolation film or paint film and the molding tool surface fit smoothly, and no wrinkles are allowed in the mold surface.

Description

technical field [0001] The invention belongs to the field of aircraft structures, and relates to a prefabricated body transfer and lamination of composite material parts and a method thereof. Background technique [0002] Narrow cavity one-way belt structural parts, composite parts with cavity width between 12mm-40mm, adopt autoclave forming process, in order to ensure the thickness of parts, adopt female mold forming, such as typical C-beam, sleeve structure, For narrow-cavity U-shaped structural parts, after paving on the forming tool, the autoclave is cured, and the cavity width is 12mm, as follows figure 1 As shown in the figure, if the female mold is directly used for forming, it is easy to produce wrinkles at the corner of the part or the root of the part during bag making; parts with a cavity width of about 40mm are directly layered on the female mold, which is also easy to produce wrinkles at the root of the part. pleated. [0003] The composite parts need to be co...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34B29C70/54
CPCB29C70/342B29C70/54
Inventor 刘望子管海新丁奇锋陈正生李军祝景萍刘洋王强余佳易卫李威
Owner JIANGXI CHANGHE AVIATION IND