CN111421859A

CN111421859A - Carbon fiber mold for manufacturing aerospace materials

Info

Publication number: CN111421859A
Application number: CN202010370057.6A
Authority: CN
Inventors: 关志东; 徐祝方
Original assignee: DANYANG DANJIN AVIATION MATERIAL TECHNOLOGY CO LTD
Current assignee: DANYANG DANJIN AVIATION MATERIAL TECHNOLOGY CO LTD
Priority date: 2020-05-06
Filing date: 2020-05-06
Publication date: 2020-07-17
Anticipated expiration: 2040-05-06
Also published as: CN111421859B

Abstract

The invention discloses a carbon fiber mould for manufacturing aerospace materials, which comprises a mould frame, wherein the mould frame comprises an upper pressing plate and a lower pressing plate, two side pressing plates are slidably connected between the upper pressing plate and the lower pressing plate, a cavity is defined by the upper pressing plate, the lower pressing plate and the side pressing plates, a core mould is placed in the cavity, a gap is formed between the core mould and the inside of the cavity, the gap is a mould cavity, a workpiece to be processed is placed in the mould cavity, the core mould is provided with four side walls, the side walls are made of carbon fiber composite plates, an elastic connecting strip is connected between two adjacent carbon fiber composite plates, a containing cavity is formed in the hollow inside of the core mould, cover plates are arranged at two ends of the core mould and can seal the containing cavity, a liquid injection port is formed in any one of the cover plates, a liquid or gaseous forming medium is input into the containing cavity through the liquid injection port, after the containing cavity is filled with the forming medium, the forming medium can enable the elastic connecting strips to expand outwards under the action of internal pressure.

Description

Carbon fiber mold for manufacturing aerospace materials

Technical Field

The invention relates to the technical field of carbon fibers, in particular to a carbon fiber mold for manufacturing aerospace materials.

Background

Some aerospace hollow parts in the prior art are formed by internal high pressure, an internal high pressure forming die generally comprises an upper die and a lower die, a die cavity is formed between the upper die and the lower die, the shape of the die cavity is set to be consistent with that of a final product, then a workpiece is placed into the die cavity, two ends of the workpiece are sealed, then internal water is filled, the workpiece is expanded outwards by utilizing hydraulic pressure until the workpiece is attached to the inner wall of the die cavity, and internal high pressure forming is completed at the moment.

However, when the workpiece is manufactured by internal high-pressure forming, it is difficult to ensure the thickness of each position to be consistent, because the workpiece is continuously expanded outwards in the internal high-pressure forming process, the larger the expansion amplitude is, the more obvious the wall thickness of the position is reduced, at present, the material supplement is generally carried out by continuously extruding the workpiece by using hydraulic cylinders on two sides, but the method is difficult to manufacture the workpiece with a standard right angle, because the workpiece with the arc-shaped corner can be formed for a plurality of times with small amplitude to ensure the roundness, but the material accumulation of the right-angle workpiece at the tip of the right angle is irreversible once the material is reduced or the material supplement amplitude is too large.

Disclosure of Invention

The invention aims to provide a carbon fiber mold which is used for manufacturing aerospace materials and can manufacture workpieces with standard right angles.

In order to achieve the purpose, the invention provides the following technical scheme:

a carbon fiber mold for manufacturing aerospace materials comprises a mold frame, wherein the mold frame comprises an upper pressing plate and a lower pressing plate, two side pressing plates are connected between the upper pressing plate and the lower pressing plate in a sliding mode, a cavity is defined by the upper pressing plate, the lower pressing plate and the side pressing plates, a core mold is placed in the cavity, a gap is formed between the core mold and the inside of the cavity and is a mold cavity, a workpiece to be processed is placed in the mold cavity, the core mold is provided with four side walls, the side walls are made of carbon fiber composite plates, an elastic connecting strip is connected between every two adjacent carbon fiber composite plates, a containing cavity is formed in the core mold in a hollow mode, cover plates are arranged at two ends of the core mold and can seal the containing cavity, a liquid injection port is formed in any one of the cover plates, and a liquid or gaseous forming medium is input into the containing cavity through the liquid injection port, after the containing cavity is filled with the forming medium, the forming medium can enable the elastic connecting strips to expand outwards under the action of internal pressure.

As an improvement of the invention, the elastic connecting strip comprises a silicon steel sheet, two sides of the silicon steel sheet are connected with the carbon fiber composite board, and the surface of the silicon steel sheet is wrapped with rubber.

As a specific technical scheme of the invention, after a workpiece is placed in a die cavity, the workpiece is clamped between the upper pressing plate, the lower pressing plate, the side pressing plate and the core die, and gaps are formed among four corners of the workpiece, the elastic connecting strips and the inner wall of the die cavity.

Compared with the prior art, the invention has the advantages that: the elastic connecting strip is driven to expand outwards by internal pressure and is formed by welding two silicon steel sheets, and the limit of outward expansion of the elastic connecting strip is that the two silicon steel sheets are perpendicular to each other, so that when the elastic connecting strip expands to the limit, an external workpiece can be pushed to expand into a right-angle shape.

Drawings

FIG. 1 is a schematic structural diagram of a carbon fiber mold for aerospace material fabrication in an embodiment of the invention;

fig. 2 is a cross-sectional view of fig. 1.

Detailed Description

The invention is described in further detail below with reference to the accompanying examples.

As shown in the accompanying drawings, the embodiment is a carbon fiber mold for aerospace material manufacturing, which comprises a mold base, wherein the mold base comprises an upper pressing plate 1 and a lower pressing plate 2, two side pressing plates 3 are slidably connected between the upper pressing plate and the lower pressing plate, grooves are formed on opposite sides of the two side pressing plates, the upper groove wall and the lower groove wall of each groove are respectively attached to the bottom surface of the upper pressing plate and the top surface of the lower pressing plate, the upper pressing plate is fixed on a press machine 8, the lower pressing plate is fixed on a mold base 4, and the press machine can provide a lower pressure to press the upper pressing plate downwards so as to tightly press the side pressing plates on the lower pressing plate.

In this embodiment, a cavity is defined by the upper platen, the lower platen and the side platens, a core mold 5 is placed in the cavity, a gap is formed between the core mold and the inside of the cavity, the gap is a mold cavity 6, a workpiece 7 to be machined is placed in the mold cavity, and the workpiece is clamped between the outer wall of the core mold and the inner wall of the cavity at positions other than four corners except for the positions of the four corners

The former has four side walls 51 made of carbon fibre composite sheet and has a relatively high stiffness making it difficult to deform during expansion. Be connected with elastic connection strip 52 between two adjacent carbon fiber composite sheet, elastic connection strip is formed by two silicon steel sheet welding, the limit that elastic connection strip outwards expands is two silicon steel sheet mutually perpendicular, so when elastic connection strip inflation to the limit, can promote outside work piece inflation one-tenth right angle shape, scrape the inner wall of colored work piece in order to prevent elastic connection strip after the inflation one-tenth right angle, wrap up rubber on elastic connection strip, this rubber is fluorine-containing rubber, can prevent that it from taking place to bond with the work piece.

The inner part of the core mold is hollow to form a containing cavity, cover plates 53 are arranged at two ends of the core mold and can seal the containing cavity, a liquid injection port 54 is formed in any one of the cover plates, a liquid or gaseous forming medium is input into the containing cavity through the liquid injection port, after the containing cavity is filled with the forming medium, the forming medium can enable the elastic connecting strips to expand outwards under the action of internal pressure until the elastic connecting strips reach the expansion limit, and workpieces are pushed by the elastic connecting strips to expand together in the expansion process of the elastic connecting strips until a standard right angle is formed.

The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may occur to those skilled in the art without departing from the principle of the invention, and are considered to be within the scope of the invention.

Claims

1. A carbon fiber mould for aerospace material manufacturing, its characterized in that: the machining device comprises a die carrier, wherein the die carrier comprises an upper pressing plate and a lower pressing plate, two side pressing plates are connected between the upper pressing plate and the lower pressing plate in a sliding mode, a cavity is defined by the upper pressing plate, the lower pressing plate and the side pressing plates, a core die is placed in the cavity, a gap is formed between the core die and the interior of the cavity and is a die cavity, a workpiece to be machined is placed in the die cavity, the core die is provided with four side walls, the side walls are made of carbon fiber composite plates, an elastic connecting strip is connected between every two adjacent carbon fiber composite plates, a containing cavity is formed in the core die in a hollow mode, cover plates are arranged at two ends of the core die and can seal the containing cavity, a liquid injection port is formed in any one of the cover plates, a liquid or gaseous forming medium is input into the containing cavity through the liquid injection port, and after the containing cavity is filled with the forming medium, the forming medium can make the elastic connecting strips expand outwards under the action of the internal pressure.

2. The carbon fiber mandrel for aerospace material manufacture of claim 1, wherein: the elastic connecting strip comprises silicon steel sheets, two sides of each silicon steel sheet are connected with the carbon fiber composite board, and rubber is wrapped on the surfaces of the silicon steel sheets.

3. The carbon fiber mandrel for aerospace material manufacture of claim 2, wherein: after a workpiece is placed in the die cavity, the workpiece is clamped between the upper pressing plate, the lower pressing plate, the side pressing plates and the core die, and gaps are formed among the four corners of the workpiece, the elastic connecting strips and the inner wall of the die cavity.