CN116021796B - H-beam structure composite material support plate and forming method and forming device thereof - Google Patents
H-beam structure composite material support plate and forming method and forming device thereof Download PDFInfo
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- CN116021796B CN116021796B CN202310027712.1A CN202310027712A CN116021796B CN 116021796 B CN116021796 B CN 116021796B CN 202310027712 A CN202310027712 A CN 202310027712A CN 116021796 B CN116021796 B CN 116021796B
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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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention relates to the technical field of composite material forming methods, in particular to an H-beam structure composite material supporting plate, a forming method and a forming device thereof, wherein the forming device of the H-beam structure composite material supporting plate comprises a base plate, split pieces, a positioning device and a pressure equalizing plate; the forming method of the H-beam structure composite material supporting plate comprises the steps of manufacturing a supporting plate forming device, preparing prepreg, assembling the forming device, laying the prepreg, curing and forming the prepreg autoclave, and removing the forming device to obtain the H-beam structure composite material supporting plate. The invention can improve the internal quality of the product and the dimension requirement of the external surface of the product, avoid the quality defect at the web position from influencing the strength requirement of the product, and ensure the precision of the external surface of the product to avoid the scrapping of the product caused by dislocation.
Description
Technical Field
The invention relates to the technical field of composite material forming methods, in particular to an H-beam structure composite material supporting plate, and a forming method and a forming device thereof.
Background
In recent years, the development of composite materials is rapid due to their excellent properties, and intensive research into composite materials has been conducted in various industrial fields such as aerospace industry and high-speed rail industry. The H-beam structure composite material part is mainly characterized by high strength, high specific modulus, low cost, light weight, short production period, higher stability and high structural efficiency, and is mainly applied to supporting structures of carrier rockets, missiles and the like. Along with the continuous development of the field of composite materials and the continuous improvement of requirements, the materials of the support structure are continuously updated, the structure is continuously optimized and more complex, and the requirements on the molding and manufacturing process of the composite structural member are also continuously improved.
At present, the common forming method of the H-beam structure of the composite material comprises the following two steps, namely a metal die-matching forming process, wherein the forming process is very easy to generate flaw detection defects due to the structural form of a product, the internal quality is influenced, the outer surface of the product is provided with steps generated when a metal outer die is matched, the mechanical property and the appearance quality of the product are greatly influenced, and the autoclave forming process is changed into the forming process, the structural form of a die and the process implementation are relatively simple, but the outer surface of the product obtained by using the forming process is provided with larger steps, the dimensional accuracy is poor, the use requirement cannot be met, and the product is very easy to discard.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, and provides an H-beam structure composite material supporting plate, a forming method and a forming device thereof, wherein the forming device of the H-beam structure composite material supporting plate improves the problem that the upper part and the lower part of an H-beam structure are easy to generate dislocation through a positioning device; the forming method of the H-beam structure composite material supporting plate can solve the problems that the operation flow of the forming process is complex and the internal quality of the H-shaped structure web plate is easy to have defects.
In order to achieve the above purpose, the present invention adopts the following specific technical scheme:
The invention provides a forming device for an H-beam structure composite material supporting plate, which comprises a base plate, split and a pressure equalizing plate, wherein the split and the base plate are assembled and installed, and the pressure equalizing plate is arranged on the periphery of the base plate and the split after being assembled and installed, so that the overall dimension of a product is ensured.
Further, the split is formed by splicing and combining a plurality of parts, and each part can be independently detached and installed, so that the product is convenient to demould.
Further, the forming device also comprises a positioning device for fixing the positions of the base plate and the split, so as to prevent dislocation during assembly.
The invention provides a forming method of an H-beam structure composite material supporting plate, which comprises the following steps:
S1, manufacturing an H-beam structure composite material supporting plate forming device;
S2, preparing a prepreg comprising a matrix material and a reinforcing material;
S3, split of the assembly forming device, wherein a web plate and a wing plate are paved on the split by using prepreg, vacuumizing and prepressing are carried out after 8-12 layers are paved, and bubbles are discharged to enable the layering of the prepreg to be more compact;
S4, fixing the positions of the base plate and the split by using a positioning device in the forming device, assembling the base plate and the split, and winding the butt joint of the split of the upper part and the split of the lower part by using prepreg;
S5, dismantling the positioning device, and paving wing plates by using prepreg;
S6, after the wing plates are laid, sequentially placing a uniform pressing plate in the forming device outside the wing plates to be tightly attached to the prepreg, so that the outline dimension of the wing plates of the product is ensured;
s7, carrying out autoclave curing molding on the prepreg;
S8, removing the base plate, splitting and equalizing the plates to obtain the H-beam structure composite material supporting plate.
Further, the matrix material is cyanate resin, the reinforcing material is T700-grade carbon fiber, and the prepreg is prepared by adopting a hot melting preparation process.
Further, the use of the prepreg to lay up the web on the split includes the steps of:
the whole supporting plate is divided into two symmetrical parts by taking the middle surface of the web plate as a symmetrical surface, prepreg is used for being independently laid, the prepreg is laid in the direction that each side of the web plate is 0 degrees, and the prepreg is laid in a lap joint mode at the corner position of the supporting plate by +/-45 degrees, so that the continuity and the overall structural strength of the fiber laying are ensured.
Further, the base plate and the split are assembled using dowel pins and bolts.
Further, the process conditions of autoclave curing molding are that the vacuum degree is not more than-0.095 MPa, the curing temperature is 130-180 ℃ and the pressure is 0.2-0.3 MPa.
The invention provides an H-beam structure composite material supporting plate which is manufactured by a forming method of the H-beam structure composite material supporting plate.
The invention can obtain the following technical effects:
the forming device provided by the invention has the advantages that the problem of dislocation easily caused by the upper part and the lower part of the H-beam structure is solved through the positioning device, the outline dimension precision of the product appearance surface is ensured through the cooperation of the equalizing plate, and the product is ensured to meet the use requirement. Meanwhile, the forming method provided by the invention can simplify the forming process and is convenient to operate, and the quality of the H-beam structural web plate is improved by adopting the autoclave forming process.
Drawings
Fig. 1 is a schematic structural view of a forming device for an H-beam structural composite support plate according to an embodiment of the present invention.
Fig. 2 is a schematic structural view of a positioning device in an H-beam structure composite support plate forming device according to an embodiment of the present invention.
Fig. 3 is a schematic view of the appearance of an H-beam structure composite support plate product manufactured by the forming method according to the embodiment of the invention.
Wherein reference numerals include:
a base plate 1, split segments 2, a pressure equalizing plate 3, a web 4 and a wing plate 5.
Detailed Description
Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings. In the following description, like modules are denoted by like reference numerals. In the case of the same reference numerals, their names and functions are also the same. Therefore, a detailed description thereof will not be repeated.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limiting the invention.
Fig. 1 shows the structure of an H-beam structure composite material support plate forming device according to an embodiment of the invention, which comprises a substrate, split, a positioning device and a equalizing plate, wherein the split is assembled with the substrate, the positioning device is used for fixing the positions of the substrate and the split, dislocation during assembly is prevented, and the equalizing plate is placed on the periphery of the assembled substrate and split, so that the overall dimension of a product is ensured.
Fig. 2 shows the structure of a positioning device in an H-beam structure composite support plate forming device according to an embodiment of the invention.
The forming device improves the problem that the upper part and the lower part of the H beam structure are easy to generate dislocation through arranging the positioning device, and ensures the outline dimension precision of the appearance surface of the product through matching with the use of the equalizing plate, thereby ensuring that the product meets the use requirement.
The invention provides a forming method of an H-beam structure composite material supporting plate, which comprises the following steps:
s1, manufacturing an H-beam structure composite material supporting plate forming device.
S2, preparing a prepreg comprising a matrix material and a reinforcing material.
The matrix material is cyanate resin, the reinforcing material is T700 grade carbon fiber, and the prepreg is prepared by adopting a hot melting preparation process.
S3, split of the assembly forming device, wherein the prepreg is used for laying webs and wing plates on the split, vacuumizing and prepressing are carried out after 8-12 layers are laid, and air bubbles are discharged to enable the prepreg to be compacter between the layers.
The use of prepreg to lay up the web on the split comprises the steps of:
the whole supporting plate is divided into two symmetrical parts by taking the middle surface of the web plate as a symmetrical surface, prepreg is used for being independently laid, the prepreg is laid in the direction that each side of the web plate is 0 degrees, and the prepreg is laid in a lap joint mode at the corner position of the supporting plate by +/-45 degrees, so that the continuity and the overall structural strength of the fiber laying are ensured.
S4, fixing the positions of the base plate and the split by using a positioning device in the forming device, assembling the base plate and the split, and winding the butt joint of the split of the upper part and the split of the lower part by using prepreg.
The base plate and the split are assembled by using a locating pin and a bolt.
S5, dismantling the positioning device, and paving wing plates by using prepreg;
S6, after the wing plates are laid, sequentially placing a uniform pressing plate in the forming device outside the wing plates to be tightly attached to the prepreg, so that the outline dimension of the wing plates of the product is ensured;
s7, carrying out autoclave curing molding on the prepreg;
The process conditions of curing and forming in the autoclave are that the vacuum degree is not more than-0.095 MPa, the curing temperature is 130-180 ℃ and the pressure is 0.2-0.3 MPa.
S8, removing the base plate, splitting and equalizing the plates to obtain the H-beam structure composite material supporting plate.
The forming method provided by the invention can simplify the forming process and is convenient to operate, and the quality of the H-beam structural web plate is improved by adopting the autoclave forming process.
Fig. 3 shows the appearance of an H-beam structure composite support plate product manufactured by the forming method according to an embodiment of the present invention.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
While embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the invention.
The above embodiments of the present invention do not limit the scope of the present invention. Any of various other corresponding changes and modifications made according to the technical idea of the present invention should be included in the scope of the claims of the present invention.
Claims (6)
1. The forming method of the H-beam structure composite material supporting plate is characterized by comprising the following steps of:
S1, manufacturing an H-beam structure composite material supporting plate forming device, which comprises a base plate, split pieces and a pressure equalizing plate, wherein the split pieces are assembled with the base plate, and the pressure equalizing plate is arranged on the periphery of the base plate and the split pieces after being assembled, so that the overall dimension of a product is ensured;
the split is formed by splicing and combining a plurality of parts, and each part can be independently detached and installed, so that the product is convenient to demould;
the forming device further comprises a positioning device for fixing the positions of the upper part of the substrate and the lower part of the substrate and the split, so that the die is prevented from being misplaced during assembly;
S2, preparing a prepreg comprising a matrix material and a reinforcing material;
s3, assembling split of the forming device, using the prepreg to lay a web plate and a wing plate on the split, vacuumizing and prepressing after laying 8-12 layers each time, and discharging bubbles to enable the prepreg layers to be more compact;
S4, fixing the positions of the upper part of the substrate and the lower part of the substrate and the split by using a positioning device in the forming device, assembling the substrate and the split, and winding the butt joint positions of the upper part and the lower part of the split by using the prepreg;
s5, removing the positioning device, and paving wing plates by using the prepreg;
S6, after the wing plates are laid, sequentially placing a uniform pressing plate in the forming device on the outer side of the wing plates to be tightly attached to the prepreg, so that the outline dimension of the wing plates of the product is ensured;
s7, carrying out autoclave curing molding on the prepreg;
S8, removing the base plate, splitting and equalizing plates to obtain the H-beam structure composite material supporting plate.
2. The method for forming a composite support plate of an H-beam structure according to claim 1, wherein in the step S2, the matrix material is cyanate resin, the reinforcing material is T700 carbon fiber, and the prepreg is prepared by a hot-melt preparation process.
3. The method of forming an H-beam structural composite support plate according to claim 1, wherein in step S3, the laying of webs on the segments using prepregs comprises the steps of:
The whole supporting plate is divided into two symmetrical parts by taking the middle surface of the web plate as a symmetrical surface, the prepregs are respectively and independently laid, the prepregs are laid in the direction of 0 DEG on each side of the web plate, and the prepregs are lap-laid at +/-45 DEG on the corner position of the supporting plate, so that the continuity and the overall structural strength of the fiber layering are ensured.
4. The method of forming an H-beam structural composite support plate according to claim 1, wherein in step S4, the base plate and the split are assembled using a dowel pin and a bolt.
5. The method for forming the H-beam structural composite material supporting plate according to claim 1, wherein in the step S7, the process conditions of the autoclave curing forming are that the vacuum degree is not more than-0.095 MPa, the curing temperature is 130-180 ℃ and the pressure is 0.2-0.3 MPa.
6. An H-beam structure composite support plate manufactured by the forming method according to any one of claims 1 to 5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310027712.1A CN116021796B (en) | 2023-01-09 | 2023-01-09 | H-beam structure composite material support plate and forming method and forming device thereof |
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| CN202310027712.1A CN116021796B (en) | 2023-01-09 | 2023-01-09 | H-beam structure composite material support plate and forming method and forming device thereof |
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| CN116021796B true CN116021796B (en) | 2025-04-01 |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111716601A (en) * | 2020-07-22 | 2020-09-29 | 哈尔滨玻璃钢研究院有限公司 | A preparation method of a large-scale main bearing composite material structure and a molding die used therefor |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4459401B2 (en) * | 2000-07-17 | 2010-04-28 | 本田技研工業株式会社 | Composite beam forming method |
| US11376801B2 (en) * | 2019-06-24 | 2022-07-05 | The Boeing Company | Composite material rework parts and methods of making composite rework parts |
| CN112123811B (en) * | 2020-07-24 | 2022-08-12 | 北京卫星制造厂有限公司 | Forming method of split tooling composite material bracket |
| CN112606434A (en) * | 2020-12-14 | 2021-04-06 | 陕西天翌天线股份有限公司 | Auxiliary forming method for thermal expansibility core die of H-shaped beam and H-shaped beam |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111716601A (en) * | 2020-07-22 | 2020-09-29 | 哈尔滨玻璃钢研究院有限公司 | A preparation method of a large-scale main bearing composite material structure and a molding die used therefor |
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