Co-curing molding process for double-sided reinforced fuselage frame of composite materials

A technology of curing molding and process method, which is applied in the field of composite material manufacturing, can solve the problems of increased manufacturing risk, long manufacturing cycle, and high production cost, and achieve the effects of improving economy and safety, low cost, and excellent product quality

Active Publication Date: 2018-05-11
COMAC +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since this type of process scheme requires at least two times of entering the autoclave to complete the manufacturing, the manufacturing cycle is long and the production cost is high
In addition, several times of entering the autoclave makes some materials stay in a high temperature environment for a long time, which increases the manufacturing risk

Method used

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  • Co-curing molding process for double-sided reinforced fuselage frame of composite materials
  • Co-curing molding process for double-sided reinforced fuselage frame of composite materials
  • Co-curing molding process for double-sided reinforced fuselage frame of composite materials

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Embodiment Construction

[0040] In the following detailed description of the preferred embodiments, reference will be made to the accompanying drawings which form a part hereof. The accompanying drawings show, by way of example, specific embodiments in which the invention can be practiced. The illustrated embodiments are not intended to be exhaustive of all embodiments in accordance with the invention. It is to be understood that other embodiments may be utilized and structural or logical modifications may be made without departing from the scope of the present invention.

[0041] like Figure 1a , 1b As shown in and 1c, the present invention takes the molding of a composite material double-sided reinforced fuselage frame structure as an example, the fuselage frame includes a laminate 3, and three longitudinal T-shaped ribs 1 are installed on the first side of the laminate 3. , two transverse T-shaped ribs 2 are installed on the second side, and the process is as follows:

[0042] (1) Manufacture o...

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Abstract

The invention provides a co-curing forming technological method for a composite fuselage frame body with ribs added to the two sides. The method comprises the steps of 1, manufacturing a soft mould forming tool; 2, manufacturing a soft mould; 3, laying, attaching and assembling the T-shaped ribs; 4, positioning the ribs of a first side; 5, laying and attaching a laminated board; 6, conducting overturning and positioning; 7, positioning the ribs of a second side; 8, making vacuum bags; 9, overturning and fixing a rigid forming tool; 10, conducting curing; and 11, conducting demoulding. By means of the co-curing forming technological method, the laminated board and the ribs at the two sides can be co-cured; curing of all components can be completed through one-step potting; manufacturing cost is lowered; the manufacturing process is simplified; and product quality can also be guaranteed.

Description

technical field [0001] The invention belongs to the field of composite material manufacturing, and in particular relates to a co-curing molding process method for a double-sided reinforced fuselage frame body of a composite material. Background technique [0002] Due to its excellent performance, composite materials have been applied to various aircraft models in different structural forms in recent years, and many frame parts in the rear section of the fuselage also use composite materials. Since these types of parts mostly use the double-sided reinforced structure of composite material laminates, the previous manufacturing process usually chooses the process plan of co-bonding or secondary bonding. That is, the laminate and the ribs on one side are co-cured first, and then the cured laminate is put into the tank again to complete the co-bonding or secondary bonding with the ribs on the other side. Since this kind of process scheme requires at least two times of entering t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/44B29C70/54
CPCB29C70/443B29C70/541
Inventor 刘军徐应强王伦倪永佳杨云仙倪佐僖宁波李颖
Owner COMAC
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