CN114030204A - Non-autoclave molding method for large-size composite material barrel - Google Patents
Non-autoclave molding method for large-size composite material barrel Download PDFInfo
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- CN114030204A CN114030204A CN202111316509.3A CN202111316509A CN114030204A CN 114030204 A CN114030204 A CN 114030204A CN 202111316509 A CN202111316509 A CN 202111316509A CN 114030204 A CN114030204 A CN 114030204A
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- 239000002131 composite material Substances 0.000 title claims abstract description 72
- 238000000034 method Methods 0.000 title claims abstract description 26
- 238000000465 moulding Methods 0.000 title claims abstract description 24
- 238000013461 design Methods 0.000 claims abstract description 16
- 239000000463 material Substances 0.000 claims abstract description 9
- 239000007769 metal material Substances 0.000 claims abstract description 6
- 238000010438 heat treatment Methods 0.000 claims description 12
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 6
- 229910045601 alloy Inorganic materials 0.000 claims description 4
- 239000000956 alloy Substances 0.000 claims description 4
- 230000007547 defect Effects 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 229910001374 Invar Inorganic materials 0.000 claims description 3
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims description 3
- 229910052742 iron Inorganic materials 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 238000007711 solidification Methods 0.000 claims description 3
- 230000008023 solidification Effects 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 238000004381 surface treatment Methods 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 2
- 239000011800 void material Substances 0.000 claims description 2
- 239000000835 fiber Substances 0.000 abstract description 17
- 238000002360 preparation method Methods 0.000 abstract description 2
- 238000007493 shaping process Methods 0.000 abstract 2
- 239000011162 core material Substances 0.000 description 40
- 239000010410 layer Substances 0.000 description 29
- 239000006260 foam Substances 0.000 description 5
- 230000003014 reinforcing effect Effects 0.000 description 5
- 208000029152 Small face Diseases 0.000 description 4
- 239000004744 fabric Substances 0.000 description 3
- 238000007796 conventional method Methods 0.000 description 2
- 238000012938 design process Methods 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 238000009745 resin transfer moulding Methods 0.000 description 2
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 1
- 235000017491 Bambusa tulda Nutrition 0.000 description 1
- 241001330002 Bambuseae Species 0.000 description 1
- 229910000737 Duralumin Inorganic materials 0.000 description 1
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 1
- 239000011425 bamboo Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000000805 composite resin Substances 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000001721 transfer moulding Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/712—Containers; Packaging elements or accessories, Packages
- B29L2031/7154—Barrels, drums, tuns, vats
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a non-autoclave molding method of a large-size composite material cylinder, which comprises the following steps: assembling a forming die; laying a composite material prepreg for forming the target cylinder on the outer surface of a core mold, and then mounting a female mold to enable the female mold and the core mold to be combined to form a forming mold cavity of the target cylinder; the core mold is heated to expand, a prepreg layer of the composite material is extruded, the thickness of the prepreg layer is equal to the design thickness of the target cylinder, and then curing treatment is carried out; and obtaining a target cylinder product. Through big coefficient of expansion metal material preparation mandrel, the thickness that makes the die cavity increases to some extent on the basis of barrel design thickness, can additionally lay multilayer preimpregnation material when laying composite material preimpregnation material, along with the mandrel is heated and expands, the thickness of shaping die cavity is compressed, the thickness that composite material preimpregnation material spread the layer is compressed to being equal with barrel design thickness, make the barrel under the prerequisite that keeps design thickness, the interlaminar pressure when the increase shaping, also increase the fibre volume fraction of product, promote mechanical properties.
Description
Technical Field
The invention relates to the technical field of composite material forming, in particular to a non-autoclave forming method of a large-size composite material cylinder.
Background
The advanced resin-based composite material has the unique advantages of higher specific strength and specific stiffness, strong designability, excellent corrosion resistance and convenience for large-area integral forming, and becomes an indispensable strategic material in high-tech equipment. The composite material can be applied to high and new equipment in a large amount, so that the performance can be effectively improved, the structural weight can be reduced, the operation cost can be reduced, and the market competitiveness can be enhanced. Currently, the prior art composite molding method is gradually shifting from a high cost autoclave molding process to a low cost Resin Transfer Molding (RTM) bulk molding technique.
The RTM process has the process characteristic of closed mold forming, the inner surface and the outer surface of a workpiece are controlled by the mold surface, so that the overall dimension precision of the workpiece is high, the integral manufacture of the workpiece with a complex structure can be realized through reasonable layering optimization and the design of a forming mold, the structural weight reduction efficiency is effectively improved, and the manufacturing and assembling cost of the composite material workpiece is reduced. However, in the prior art, the size of the mold adopted by the RTM process is designed correspondingly according to the cylinder to be molded, i.e., the thickness of the cavity in the mold is equal to the thickness of the cylinder. If the dry fiber fabric is paved and then the glue is injected for preparation, the paving layer number has to be reduced in order to plug the fabric paving layer into the female die due to the loose dry fiber fabric paving layer, namely the fiber volume fraction of the target product is reduced; if the prepreg is laid, the fiber volume fraction is improved, but interlayer pressurization cannot be carried out during curing molding, and defects such as looseness, gaps and the like can be caused to influence the performance of the product. In most use scenes, the thickness, the mechanical property and the like of the cylinder body have hard requirements, such as rocket cabin sections.
Disclosure of Invention
Aiming at the problem that the high mechanical property requirement and the low cost requirement of the composite material cylinder body in the prior art cannot be considered at the same time, the invention provides a non-autoclave molding method of a large-size composite material cylinder body, so that the mechanical property of the cylinder body is greatly improved on the premise of keeping low cost.
In order to achieve the purpose, the invention provides a non-autoclave molding method of a large-size composite material cylinder, which comprises the following steps:
step 1, assembling a forming die, wherein the forming die comprises a female die and a core die, the female die is made of a near-zero expansion material, and the core die is a rigid die made of a metal material with a large expansion coefficient;
step 2, after the surface treatment and detection of the forming mold are completed, laying the composite prepreg for forming the large-size composite material cylinder on the outer surface of the core mold, then installing a female mold, combining the female mold and the core mold to form a forming mold cavity of a target cylinder, and coating all composite material prepreg layers, wherein the initial thickness of the composite material prepreg layers is larger than the design thickness of the large-size composite material cylinder as the overall dimension of the core mold is reduced compared with the internal dimension of a target product;
and 4, removing the female die and the core die to obtain a large-size composite material barrel product.
In one embodiment, the core mold is a hollow structure, the external dimension of the core mold is reduced to a smaller extent than the size of the inner cavity of the target cylinder body, and a heating tool is preset in the core mold.
In one of the embodiments, the female mold is made of invar alloy or carbon fiber composite.
In one embodiment, the mandrel is made of steel, iron, or aluminum.
In one embodiment, the large-size composite material cylinder is in a cylindrical structure or a conical cylinder or a prismatic cylinder structure.
In one embodiment, in the step 2, the composite prepreg for forming the large-size composite material cylinder is paved on the outer surface of the core mold layer by layer, and air is expelled by a paving tool in the paving process of each layer of prepreg, so that the occurrence of pore defects between the composite layers is prevented.
In one embodiment, the specific process in step 3 is as follows:
and (3) putting the forming die into an oven, opening a heating tool arranged in the core die at first to ensure that the core die is heated to a set temperature according to a plan, expanding and maintaining the pressure for a certain period of time, then starting the oven to heat to the set temperature, preserving the heat for solidification, then naturally cooling to the room temperature, and then demoulding.
According to the non-autoclave molding method of the large-size composite material cylinder provided by the invention, the core mold prepared from the metal material with the large expansion coefficient enables the thickness of the molding cavity to be slightly increased on the basis of the design thickness of the cylinder in the design process of the molding mold, so that multiple layers of prepreg can be additionally laid when the composite material prepreg is laid, the thickness of the molding cavity is slightly compressed along with the expansion of the core mold due to the fact that the female mold is not expanded, the thickness of the composite material prepreg is compressed to be equal to the design thickness of the cylinder, and compared with the cylinder molded by a conventional method, the fiber volume fraction and the strength of the cylinder are greatly improved on the premise of keeping the target thickness due to the fact that the multiple layers of prepreg are additionally laid.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic flow chart of a non-autoclave molding method for a large-sized composite material cylinder according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a forming mold for a large-sized composite material cylinder according to an embodiment of the present invention;
fig. 3 is a schematic view showing the entire structure of a core mold in an embodiment of the present invention;
fig. 4 is a sectional view showing the entire structure of the core mold in the embodiment of the present invention.
Reference numerals: the die comprises a female die 1, a core die 2, a main body 201, a reinforcing plate 202, a support frame 203, a support shaft 204, a skirt 205, a backing plate 206, a fixing ring 207, an expansion layer 208, a first end cover 3, a first through hole 301, a second end cover 4, a second through hole 301 and a heating tool 5.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
Fig. 1 shows a non-autoclave molding method for a large-size composite material cylinder disclosed in this embodiment, which specifically includes the following steps:
step 1, assembling a forming die, wherein the forming die comprises a female die 1 and a core die 2, the female die 1 can be a split type assembling die or an integral die, the core die 2 is a rigid die made of a metal material with a large expansion coefficient, and the female die 1 has no expansion performance or the expansion coefficient of the female die 1 can be ignored;
step 2, after the surface treatment and detection of the forming mold are finished, laying the composite prepreg for forming the large-size composite material cylinder on the outer surface of the core mold 2, then installing the female mold 1, combining the female mold 1 and the core mold 2 to form a forming mold cavity of a target cylinder, and coating all composite prepreg layers, wherein the initial thickness of the composite prepreg layers is larger than the design thickness of the large-size composite material cylinder;
and 4, removing the female die 1 and the core die 2 to obtain a large-size composite material barrel product.
The mandrel 2 that this embodiment was prepared through big coefficient of expansion metal material, make forming die can increase the thickness of die cavity on the basis of barrel design thickness slightly in design process, and then can additionally lay multilayer prepreg when laying composite prepreg, and be expanded along with mandrel 2 is heated, and because bed die 1 does not expand, make the thickness of die cavity compressed slightly, make the thickness that composite prepreg laid the layer compressed to be equal with barrel design thickness, the product that obtains at last compares in the fashioned barrel of adoption conventional method, because multilayer prepreg has additionally been laid, make the barrel under the prerequisite that keeps low thickness, promote its intensity greatly.
In this embodiment, the large-sized composite material cylinder has a cylindrical structure, a tapered cylinder structure, or a prismatic cylinder structure. Referring to fig. 2, taking a forming mold of a conical cylinder as an example, the forming mold in the present embodiment includes a first end cap 3, a second end cap 4, a female mold 1 and a core mold 2, wherein the core mold 2 is a hollow cylindrical structure, and a heating tool 5 is disposed inside the core mold 2. The one end of bed die 1, the one end of mandrel 2 all links to each other with first end cover 3, the other end of bed die 1, the other end of mandrel 2 all links to each other with second end cover 4, and enclose into the one-tenth die cavity of awl tubular structure between bed die 1 and the mandrel 2, the thickness in this one-tenth die cavity is greater than the design thickness of a toper section of thick bamboo, be equipped with on the first end cover 3 with the communicating first through-hole in one end top of one-tenth die cavity, be equipped with on the second end cover 4 with the communicating second through-hole in one end below of one-tenth die cavity, in order to be used for the injecting glue.
Referring to fig. 3 to 4, in a specific implementation process, the core mold 2 includes a frame of a conical cylindrical structure and an expansion layer 208, wherein the frame includes a main body 201 of a hollow conical cylindrical structure and a plurality of reinforcing plates 202 arranged inside the main body 201, the reinforcing plates 202 are of an annular structure and are arranged in the main body 201 at intervals along an axis of the main body 201, an outer annular wall surface of each reinforcing plate 202 is attached to an inner wall surface of the main body 201 and welded into a whole, and the heating tool is supported on an inner ring of the reinforcing plate 202. The main body 201 is provided at both ends thereof with support brackets 203, and the support brackets 203 are provided with support shafts 204 for mounting the main body 201 on an external support device. The large-face end of the main body 201 is provided with a skirt 205 extending outwards, the expansion layer 208 is of a cone-shaped structure and is sleeved on the main body 201, specifically, the large-face end of the expansion layer 208 abuts against the skirt 205 through a backing plate 206, the small-face end of the expansion layer 208 is flush with the small-face end of the main body 201, and a connecting gap between the small-face end of the expansion layer 208 and the small-face end of the main body 201 is covered with a fixing ring 207 through a bolt. By forming the mandrel with a double-layer structure by the expansion layer 208 and the main body 201, the expansion amplitude of the expansion layer 208 can be corrected by the main body 201, and the mandrel can expand more uniformly when being heated. Wherein, the expansion layer 208 is formed by splicing a plurality of arc-shaped plates.
In this embodiment, the female mold 1 is made of near-zero expansion materials such as invar alloy and carbon fiber composite material, so that the female mold 1 has non-expansion performance.
In this embodiment, the core mold 2 is made of a material having a large expansion coefficient, such as steel, iron, or a duralumin alloy.
In step 2, the composite prepreg for molding the large-size composite cylinder is laid on the outer surface of the core mold 2, specifically: multiple layers of first fiber prepregs are laid on the outer surface of the core mold 2, a foam core material is laid on the uppermost layer of first fiber prepregs, and multiple layers of second fiber prepregs are laid on the foam core material. Resin layers are arranged between the first fiber prepreg and the first fiber prepreg, between the first fiber prepreg and the foam core material, between the foam core material and the second fiber prepreg and between the second fiber prepreg and the second fiber prepreg. In a preferred embodiment, air is expelled by the paving tool during the paving process of the first fiber prepreg, the foam core material and the second fiber prepreg, so that void defects between the composite layers are prevented.
The heating and curing process in the step 3 specifically comprises the following steps: and (3) putting the forming die into an oven, starting a built-in heating system of the core die at first to ensure that the core die is heated to a set temperature according to a plan, expanding, maintaining the pressure for a certain period of time, starting the oven to heat to the set temperature, preserving the heat for solidification, naturally cooling to room temperature, and then demoulding.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (7)
1. A non-autoclave molding method of a large-size composite material cylinder is characterized by comprising the following steps:
step 1, assembling a forming die, wherein the forming die comprises a female die and a core die, the female die is made of a near-zero expansion material, and the core die is a rigid die made of a metal material with a large expansion coefficient;
step 2, after the surface treatment and detection of the forming mold are finished, laying the composite prepreg for forming the large-size composite material cylinder on the outer surface of the core mold, then installing a female mold, combining the female mold and the core mold to form a forming mold cavity of a target cylinder, and coating all composite material prepreg layers, wherein the initial thickness of the composite material prepreg layers is larger than the design thickness of the large-size composite material cylinder;
step 3, heating the core mold to enable the core mold to be heated and expanded, extruding the prepreg paving layer of the composite material to enable the thickness of the prepreg paving layer to be equal to the design thickness of the large-size composite material cylinder, and then carrying out curing treatment to enable the large-size composite material cylinder to be molded;
and 4, removing the female die and the core die to obtain a large-size composite material barrel product.
2. The non-autoclave molding method of a large-sized composite material cylinder according to claim 1, wherein the core mold is a hollow structure, the outer dimension of the core mold is reduced from the inner dimension of the target cylinder, and a heating tool is preset in the core mold.
3. The non-autoclave molding method of a large-sized composite material cylinder according to claim 1, wherein the female mold is made of invar alloy or carbon fiber composite material.
4. The non-autoclave molding method of a large-sized composite material cylinder according to claim 1, wherein the core mold is made of steel, iron, or aluminum.
5. The non-autoclave molding method of the large-size composite material cylinder according to claim 1, 2, 3 or 4, wherein the large-size composite material cylinder is a cylindrical structure or a conical cylinder or a prismatic structure.
6. The non-autoclave molding method for the large-size composite material cylinder according to claim 1, 2, 3 or 4, characterized in that in the step 2, the composite material prepreg for molding the large-size composite material cylinder is laid on the outer surface of the core mold layer by layer, and air is expelled by a laying tool during laying of each layer of prepreg, so that void defects between the composite material layers are prevented.
7. The non-autoclave molding method for the large-size composite material cylinder according to claim 1, 2, 3 or 4, wherein the specific process in the step 3 is as follows:
and (3) putting the forming die into an oven, opening a heating tool arranged in the core die at first to ensure that the core die is heated to a set temperature according to a plan, expanding and maintaining the pressure for a certain period of time, then starting the oven to heat to the set temperature, preserving the heat for solidification, then naturally cooling to the room temperature, and then demoulding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111316509.3A CN114030204A (en) | 2021-11-08 | 2021-11-08 | Non-autoclave molding method for large-size composite material barrel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111316509.3A CN114030204A (en) | 2021-11-08 | 2021-11-08 | Non-autoclave molding method for large-size composite material barrel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114030204A true CN114030204A (en) | 2022-02-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111316509.3A Pending CN114030204A (en) | 2021-11-08 | 2021-11-08 | Non-autoclave molding method for large-size composite material barrel |
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| CN (1) | CN114030204A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114434743A (en) * | 2022-02-16 | 2022-05-06 | 长春长光宇航复合材料有限公司 | Preparation mold and preparation method of integrated composite material spray pipe |
| CN114559681A (en) * | 2022-02-22 | 2022-05-31 | 江苏集萃碳纤维及复合材料应用技术研究院有限公司 | Carbon fiber tubular beam forming process with variable outer diameter and thickness |
| CN116135819A (en) * | 2023-02-10 | 2023-05-19 | 中南大学 | Preparation method and application of ultra-thin carbon-ceramic composite material spray pipe extension section |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106182805A (en) * | 2016-09-09 | 2016-12-07 | 西安爱生技术集团公司 | A kind of manufacturing process of the isometrical tubular structure of carbon fibre composite |
| CN109367054A (en) * | 2018-11-07 | 2019-02-22 | 昌河飞机工业（集团）有限责任公司 | A kind of forming method of the narrow chamber shape tube beam class composite element of heavy wall |
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2021
- 2021-11-08 CN CN202111316509.3A patent/CN114030204A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106182805A (en) * | 2016-09-09 | 2016-12-07 | 西安爱生技术集团公司 | A kind of manufacturing process of the isometrical tubular structure of carbon fibre composite |
| CN109367054A (en) * | 2018-11-07 | 2019-02-22 | 昌河飞机工业（集团）有限责任公司 | A kind of forming method of the narrow chamber shape tube beam class composite element of heavy wall |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114434743A (en) * | 2022-02-16 | 2022-05-06 | 长春长光宇航复合材料有限公司 | Preparation mold and preparation method of integrated composite material spray pipe |
| CN114434743B (en) * | 2022-02-16 | 2023-05-16 | 长春长光宇航复合材料有限公司 | Preparation mold and preparation method of integrated composite material spray pipe |
| CN114559681A (en) * | 2022-02-22 | 2022-05-31 | 江苏集萃碳纤维及复合材料应用技术研究院有限公司 | Carbon fiber tubular beam forming process with variable outer diameter and thickness |
| CN116135819A (en) * | 2023-02-10 | 2023-05-19 | 中南大学 | Preparation method and application of ultra-thin carbon-ceramic composite material spray pipe extension section |
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