CN116214957A - Combined type all-carbon fiber honeycomb core structure forming tool and using method - Google Patents
Combined type all-carbon fiber honeycomb core structure forming tool and using method Download PDFInfo
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- CN116214957A CN116214957A CN202211640655.6A CN202211640655A CN116214957A CN 116214957 A CN116214957 A CN 116214957A CN 202211640655 A CN202211640655 A CN 202211640655A CN 116214957 A CN116214957 A CN 116214957A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02T50/40—Weight reduction
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Abstract
The invention provides a combined type all-carbon fiber honeycomb core structure forming tool and a using method, which relate to the technical field of composite material forming. According to the invention, a silicon rubber core mould, a metal core mould and a core mould baffle are taken as structural units, and a single honeycomb core forming tool can be used as a standard component for repeated use; through the combination of a plurality of structural units, the carbon fiber honeycomb core structure with different sizes can be designed and formed by matching with an outer die assembly and an upper pressing plate and a lower pressing plate with corresponding sizes; the core mould is designed into a combined structure form of a silicon rubber core mould and a metal core mould, so that the carbon fiber honeycomb core structure can be molded by adopting conventional heating equipment, the tool applicability is better, and the product manufacturing cost is low.
Description
Technical Field
The invention relates to the technical field of composite material forming, in particular to a combined type all-carbon fiber honeycomb core structure forming tool and a using method thereof.
Background
Structural weight reduction is the focus of spacecraft structural design. Two basic weight reduction measures include the selection of light-weight and high-strength materials and the selection of light-weight configurations. The fiber resin matrix composite is a light-weight and high-strength material and is widely applied to the structure of spaceflight carrier aircrafts. However, the contradiction between large scale and ultra-light structure of the new generation of aviation spacecraft requires the structure to comprehensively apply the two weight reduction measures, so that the structure spans from light weight to ultra-light weight. The advanced composite material grid structure is a novel composite material structure technology and meets the two requirements of an ultra-light structure. On the material selection, the structure adopts a light and high-strength continuous fiber-resin matrix composite material; the structure is porous in configuration, is similar to a net rack, and has a superior lightweight configuration.
Because the formation of the advanced resin matrix composite material and the formation of the product are carried out simultaneously, the product performance and the manufacturing process are closely related, and the discontinuity of the appearance of the grid structure makes the manufacturing process more complex than that of the composite material structure with continuous appearance, and the die cost is higher. Making the manufacturing technology one of the key technologies of advanced composite material grid structures.
The all-carbon fiber honeycomb core structure has the advantages of higher specific strength, higher specific rigidity, lower density, extremely low thermal expansion coefficient, high stability of structural performance, strong designability and the like, the design of all-carbon fiber sandwich plates is started internationally, the core structure is designed by using carbon fiber layering, and the development trend of the honeycomb structure is realized by using high-performance carbon fiber composite materials.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a combined type all-carbon fiber honeycomb core structure forming tool and a using method thereof.
The invention provides a combined type all-carbon fiber honeycomb core structure forming tool which comprises an outer die assembly, a metal core die, a core die baffle plate, an upper pressing plate, a lower pressing plate, a silicone rubber core die and fastening screws, wherein the silicone rubber core die is connected to the metal core die;
and taking the metal core mould, the core mould baffle plate and the silicon rubber core mould as structural units, and forming an all-carbon fiber honeycomb core structure by matching the outer mould assembly with the upper and lower pressing plates by the plurality of structural units.
Preferably, the silicone rubber core is mounted on the surface of the metal core.
Preferably, the core mold baffles are mounted to the upper and lower ends of the metal core mold by fastening screws.
Preferably, the outer mold assembly is mounted to the outside of the metal core mold by means of a fastening screw.
Preferably, the upper and lower press plates are mounted on the upper and lower surfaces of the outer mold assembly by fastening screws.
Preferably, the core mold baffle is provided with a limiting boss, the limiting boss is connected with the fiber clamping groove on the upper pressing plate and the lower pressing plate in an adaptive manner, and the core mold baffle is limited through the upper pressing plate and the lower pressing plate.
Preferably, the volume expansion force of the silicone rubber core mold is 0.5-3Mpa.
Preferably, the calculation formula of the volume expansion force of the silicone rubber core mold is =volume elastic modulus (silicone rubber casting volume (1+total volume expansion amount)/product cavity volume-1).
The invention also provides a use method of the combined all-carbon fiber honeycomb core structure forming tool, which comprises the following steps:
s1, mounting a silicon rubber core mould on the surface of a metal core mould to form a core mould structure;
s2, paving carbon fiber/resin composite materials on the outer surface of the core mold structure according to a designed layering mode and materials;
s3, mounting the core mold baffle plate on the upper end surface and the lower end surface of the core mold structure through fastening screws to form a single carbon fiber honeycomb core structure;
s4, after the single or a plurality of carbon fiber honeycomb cores are combined according to a design structure, an outer die assembly is installed on the outer side of the core die structure by adopting a fastening screw;
s5, installing an upper pressing plate and a lower pressing plate on the upper surface and the lower surface of the tool assembly, wherein the upper pressing plate and the lower pressing plate provide limit for the core mold baffle plate and are installed on the upper surface and the lower surface of the outer mold assembly through fastening screws.
S6, placing the product assembled in the S5 into curing equipment for curing, so that the production and manufacture of the all-carbon fiber honeycomb core structure can be realized.
Compared with the prior art, the invention has the following beneficial effects:
according to the invention, a silicon rubber core mould, a metal core mould and a core mould baffle are taken as structural units, and a single honeycomb core forming tool can be used as a standard component for repeated use; through the combination of a plurality of structural units, the carbon fiber honeycomb core structure with different sizes can be designed and formed by matching with an outer die assembly and an upper pressing plate and a lower pressing plate with corresponding sizes; the core mould is designed into a combined structure form of a silicon rubber core mould and a metal core mould, so that the carbon fiber honeycomb core structure can be molded by adopting conventional heating equipment, the tool applicability is better, and the product manufacturing cost is low.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is an exploded view of a partial structure of the present invention;
FIG. 2 is a partial cross-sectional view of FIG. 1;
FIG. 3 is a top view of the hidden upper and lower platens of the present invention.
Reference numerals in the drawings:
the metal core mould comprises an outer mould assembly 1, a metal core mould 2, a core mould baffle plate 3, an upper pressing plate 4, a lower pressing plate 4, a silicon rubber core mould 5 and fastening screws 6.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
Example 1
According to the combined type all-carbon fiber honeycomb core structure forming tool provided by the invention, as shown in fig. 1-3, the combined type all-carbon fiber honeycomb core structure forming tool comprises an outer die assembly 1, a metal core die 2, a core die baffle 3, an upper pressing plate 4, a lower pressing plate 4, a silicone rubber core die 5 and fastening screws 6, wherein the silicone rubber core die 5 is arranged on the surface of the metal core die 2, the core die baffle 3 is arranged at the upper end and the lower end of the metal core die 2 through the fastening screws 6, the outer die assembly 1 is arranged at the outer side of the metal core die 2 through the fastening screws 6, and the upper pressing plate 4 and the lower pressing plate 4 are arranged on the upper surface and the lower surface of the outer die assembly 1 through the fastening screws 6. Preferably, a limiting boss is arranged on the core mold baffle plate 3 and is connected with a fiber clamping groove on the upper pressing plate 4 in an adaptive manner, and the core mold baffle plate 3 is limited through the upper pressing plate 4 and the lower pressing plate 4. The metal core mold 2, the core mold baffle 3 and the silicone rubber core mold 5 are taken as structural units, and a plurality of structural units form an all-carbon fiber honeycomb core structure through the cooperation of the outer mold assembly 1 and the upper and lower pressing plates 4.
The metal core mold 2 is made of 45# steel. The silicon rubber core mold 5 is made of silicon rubber, and the tool size can be designed according to the wall thickness of the honeycomb core structure and the size and the number of the honeycomb cells. The linear expansion coefficient of the silicone rubber at the temperature difference of 100 ℃ is 0.00028, the total volume expansion amount is 8.64%, the bulk elastic modulus is 270Mpa, the calculation formula of the expansion force (Mpa) of the silicone rubber core die body is =bulk elastic modulus (casting volume of the silicone rubber (1+total volume expansion amount)/product cavity volume-1), and the bulk expansion force of the silicone rubber core die is optimally selected from 0.5 to 3Mpa.
Example 2
The invention also provides a composition method of the combined all-carbon fiber honeycomb core structure forming tool, as shown in figures 1-3, comprising the following steps:
s1, a silicone rubber core mold 5 is arranged on the surface of a metal core mold 2 to form a core mold structure, the combination of the silicone rubber core mold 5 and the metal core mold 2 can control the curing pressure during the molding of the carbon fiber honeycomb core structure by designing the expansion amount of the silicone rubber core mold 5, the calculation formula of the expansion force (Mpa) of the silicone rubber core mold body is =body elastic modulus (casting volume of silicone rubber (1+total volume expansion amount)/product cavity volume-1), and the body expansion force of the silicone rubber core mold 5 is selected to be optimal in 0.5-3 Mpa;
s2, paving carbon fiber/resin composite materials on the outer surface of the core mold structure according to a designed paving mode and materials, wherein the paving angle is in quasi-isotropic symmetrical paving according to [ (0 degree/90 degree/+45 degree/-45 degree] or [0 degree/+60 degree/-60 degree ], the materials are required to be tightly attached to the surface of the silicone rubber core mold 5 during paving, and the materials are not higher than the upper end surface and the lower end surface of the core mold;
s3, mounting the core mold baffle plate 3 on the upper end surface and the lower end surface of the core mold structure through fastening screws to form a single carbon fiber honeycomb core structure, wherein the core mold baffle plate 3 provides the upper end surface and the lower end surface with good carbon fiber core structure, and the limiting boss on the core mold baffle plate 3 can ensure the wall thickness dimensional precision and uniformity of the carbon fiber core structure;
s4, after single or multiple carbon fiber honeycomb cores are combined according to a design structure, an outer die assembly 1 is installed on the outer side of the core die structure by adopting a fastening screw 6, and the outer die assembly 1 provides lateral pressure when the carbon fiber core structure is formed, so that the final external dimension and the internal cementing quality of the carbon fiber core structure are ensured;
s5, installing an upper pressing plate 4 and a lower pressing plate 4 on the upper surface and the lower surface of the tool assembly, designing fiber clamping grooves on the upper pressing plate 4 and the lower pressing plate 4, providing limit for the core mold baffle 3, guaranteeing the position precision of each carbon fiber honeycomb core, and installing the upper pressing plate 4 and the lower pressing plate 4 on the upper surface and the lower surface of the outer mold assembly 1 through fastening screws 6.
S6, placing the product assembled in the S5 into curing equipment for curing, so that the production and manufacture of the all-carbon fiber honeycomb core structure can be realized.
In the description of the present application, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (9)
1. The combined type all-carbon fiber honeycomb core structure forming tool is characterized by comprising an outer die assembly (1), a metal core die (2), a core die baffle plate (3), an upper pressing plate (4), a silicon rubber core die (5) and fastening screws (6), wherein the silicon rubber core die (5) is connected to the metal core die (2), and the outer die assembly (1), the core die baffle plate (3) and the upper pressing plate (4) are respectively connected to the metal core die (2) through the fastening screws (6);
the metal core mould (2), the core mould baffle (3) and the silicon rubber core mould (5) are structural units, and the plurality of structural units form an all-carbon fiber honeycomb core structure through the matching of the outer mould assembly (1) and the upper and lower pressing plates (4).
2. The combined all-carbon fiber honeycomb core structure forming tool according to claim 1, wherein the silicone rubber core mold (5) is installed on the surface of the metal core mold (2).
3. The combined type all-carbon fiber honeycomb core structure forming tool according to claim 1, wherein the core mold baffle plate (3) is mounted at the upper end and the lower end of the metal core mold (2) through the fastening screw (6).
4. The combined all-carbon fiber honeycomb core structure forming tool according to claim 1, wherein the outer mold assembly (1) is mounted outside the metal core mold (2) through the fastening screw (6).
5. The combined all-carbon fiber honeycomb core structure forming tool according to claim 1, wherein the upper and lower pressing plates (4) are mounted on the upper and lower surfaces of the outer die assembly (1) through the fastening screws (6).
6. The combined all-carbon fiber honeycomb core structure forming tool according to claim 1, wherein a limiting boss is arranged on the core mold baffle plate (3), the limiting boss is connected with a fiber clamping groove on the upper pressing plate (4) in an adaptive manner, and the core mold baffle plate (3) is limited through the upper pressing plate (4) and the lower pressing plate (4).
7. The combined type all-carbon fiber honeycomb core structure forming tool according to claim 1, wherein the body expansion force of the silicone rubber core mold (5) is 0.5-3Mpa.
8. The combined all-carbon fiber honeycomb structure forming tool according to claim 7, wherein the calculation formula of the body expansion force of the silicone rubber core mold (5) is =body elastic modulus (silicone rubber casting volume (1+total volume expansion amount)/product cavity volume-1).
9. A method of using the combined all-carbon-fiber honeycomb core structure forming tool according to any one of claims 1 to 8, comprising the steps of:
s1, mounting the silicon rubber core mould (5) on the surface of the metal core mould (2) to form a core mould structure;
s2, paving carbon fiber/resin composite materials on the outer surface of the core mold structure according to a designed layering mode and materials;
s3, mounting the core mould baffle plate (3) on the upper end surface and the lower end surface of the core mould structure through the fastening screw (6) to form a single carbon fiber honeycomb core structure;
s4, after single or multiple carbon fiber honeycomb cores are combined according to a design structure, the outer die assembly (1) is installed outside the core die structure by adopting the fastening screw (6);
s5, the upper and lower pressing plates (4) are arranged on the upper surface and the lower surface of the tool assembly, the upper and lower pressing plates (4) provide limit for the core mold baffle plate (3), and the upper and lower surfaces of the outer mold assembly (1) are arranged through the fastening screws (6).
S6, placing the product assembled in the S5 into curing equipment for curing, so that the production and manufacture of the all-carbon fiber honeycomb core structure can be realized.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211640655.6A CN116214957A (en) | 2022-12-20 | 2022-12-20 | Combined type all-carbon fiber honeycomb core structure forming tool and using method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211640655.6A CN116214957A (en) | 2022-12-20 | 2022-12-20 | Combined type all-carbon fiber honeycomb core structure forming tool and using method |
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| CN116214957A true CN116214957A (en) | 2023-06-06 |
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| CN202211640655.6A Pending CN116214957A (en) | 2022-12-20 | 2022-12-20 | Combined type all-carbon fiber honeycomb core structure forming tool and using method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118046597A (en) * | 2024-04-15 | 2024-05-17 | 上海复合材料科技有限公司 | Composite material sandwich structure and forming method thereof |
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2022
- 2022-12-20 CN CN202211640655.6A patent/CN116214957A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118046597A (en) * | 2024-04-15 | 2024-05-17 | 上海复合材料科技有限公司 | Composite material sandwich structure and forming method thereof |
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