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Two-end closing tubular composite material component forming method

A composite material and molding method technology, which is applied in the field of manufacturing tubular special-shaped composite material parts, can solve problems such as difficult demoulding, and achieve the effects of low cost, guaranteed rigidity of the mold, and easy operation

Inactive Publication Date: 2020-09-22
AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The invention proposes a molding method of a tubular composite material part closed at both ends, which solves the problem of difficult demoulding of the tubular composite material part closed at both ends

Method used

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  • Two-end closing tubular composite material component forming method

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Embodiment Construction

[0031] Embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings and examples. The detailed description and accompanying drawings of the following embodiments are used to illustrate the principles of the present invention, but cannot be used to limit the scope of the present invention, that is, the present invention is not limited to the described embodiments, without departing from the spirit of the present invention Any modification, substitution and improvement of parts, components and connection methods are covered under.

[0032] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other.

[0033] see Figure 1 to Figure 6 , the embodiment of the present invention provides a method for forming a tubular composite material part closed at both ends. The molding method is to form a tubular fusible mold 4...

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Abstract

The invention relates to a two-end closing tubular composite material component forming method. According to the forming method, a tubular meltability die is formed in a cavity of an auxiliary die formed through tubular combination of an upper die and a lower die, and the outer profile of the cavity of the auxiliary die is the same with the inner profile of a tubular composite material component.The two-end closing tubular composite material component is prepared through the tubular meltability die, after the tubular composite material component is formed, heating is conducted to make the tubular meltability die softened, and then demoulding is finished. Demoulding is achieved through the glass transition temperature difference of the tubular meltability die and the tubular composite material component, usage of a metal combined die is avoided, the die manufacturing cost and manufacturing difficulty are reduced, thermoplastic plastics used in the meltability die have the characteristic of being recyclable, repeated usage can be achieved, and the method has the characteristics of being simple and convenient to operate, low in cost and the like.

Description

technical field [0001] The invention relates to the technical field of manufacturing tubular special-shaped composite material parts, in particular to a forming method of a tubular composite material part with both ends closed. Background technique [0002] Resin-based composite materials are widely used in aerospace and other fields, and the application structure is becoming more and more complex. Columnar composite parts, as a main structural form, are used to replace traditional metal structures such as pillars and frames to reduce structural weight. The columnar composite material structure includes: hollow tubular composite material structure, core material filled columnar structure, etc. The hollow tubular structure is a type of form that is widely used in the aerospace field, but when designing and manufacturing such structural parts, most of them use male molds Therefore, the hollow tubular structure generally requires a certain draft angle to enable the part to be ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/34B29C70/54B29C33/20B29L23/00
CPCB29C70/342B29C70/54B29C33/20B29L2023/00
Inventor 崔海超翟全胜苗春卉张洋刘立朋
Owner AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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