CN108688195B - Trapezoidal skeleton structure of carbon fiber composite material and forming method thereof - Google Patents
Trapezoidal skeleton structure of carbon fiber composite material and forming method thereof Download PDFInfo
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- CN108688195B CN108688195B CN201810609725.9A CN201810609725A CN108688195B CN 108688195 B CN108688195 B CN 108688195B CN 201810609725 A CN201810609725 A CN 201810609725A CN 108688195 B CN108688195 B CN 108688195B
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- 238000000034 method Methods 0.000 title claims abstract description 28
- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 25
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 25
- 239000002131 composite material Substances 0.000 title claims abstract description 24
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 24
- 238000000465 moulding Methods 0.000 claims abstract description 12
- 229920002379 silicone rubber Polymers 0.000 claims abstract description 11
- 238000001723 curing Methods 0.000 claims description 23
- 239000004744 fabric Substances 0.000 claims description 23
- 230000003014 reinforcing effect Effects 0.000 claims description 12
- 239000004033 plastic Substances 0.000 claims description 11
- 229910052751 metal Inorganic materials 0.000 claims description 9
- 239000002184 metal Substances 0.000 claims description 9
- AZDRQVAHHNSJOQ-UHFFFAOYSA-N alumane Chemical group [AlH3] AZDRQVAHHNSJOQ-UHFFFAOYSA-N 0.000 claims description 7
- 238000007789 sealing Methods 0.000 claims description 6
- 238000004140 cleaning Methods 0.000 claims description 3
- -1 polytetrafluoroethylene Polymers 0.000 claims description 3
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 3
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 3
- 239000003795 chemical substances by application Substances 0.000 claims description 2
- 239000007787 solid Substances 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 239000004945 silicone rubber Substances 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 4
- 230000002787 reinforcement Effects 0.000 description 4
- 239000000853 adhesive Substances 0.000 description 3
- 230000001070 adhesive effect Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
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
- B29C70/342—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 using isostatic pressure
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16S—CONSTRUCTIONAL ELEMENTS IN GENERAL; STRUCTURES BUILT-UP FROM SUCH ELEMENTS, IN GENERAL
- F16S3/00—Elongated members, e.g. profiled members; Assemblies thereof; Gratings or grilles
- F16S3/06—Assemblies of elongated members
- F16S3/08—Assemblies of elongated members forming frameworks, e.g. gratings
-
- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- General Engineering & Computer Science (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
- Reinforced Plastic Materials (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
Abstract
The invention relates to a trapezoid framework structure of a carbon fiber composite material and a forming method thereof, wherein the trapezoid framework structure adopts a form of 'block paving and combination curing', a front beam front, a front beam rear, a rear beam front, a rear beam rear and 4 rib boxes are paved respectively, and then a die is combined and enters an autoclave for curing. The forming dies behind the front beam and the rear beam adopt a combined form, so that the trapezoidal framework is ensured to be smoothly demoulded; the fixture design form of positioning stop blocks and bolt fastening is adopted, so that the positioning accuracy of the 4 rib boxes is ensured. The pressurizing mode of the front beam, the rear beam, the front rib box and the rib box adopts a silicone rubber soft film pressurizing method, so that the uniformity of the pressure of the internal complex structure and the quality of the internal surface are ensured. The co-curing molding process of the trapezoid framework of the carbon fiber composite material greatly reduces the number of fasteners and the cementing procedure, realizes the integrated molding from the structural design to the manufacture of the composite material, further reduces the weight of the trapezoid framework and improves the production efficiency.
Description
Technical Field
The invention relates to the technical field of carbon fibers, in particular to a trapezoid framework structure of a carbon fiber composite material and a forming method thereof.
Background
The carbon fiber composite material has the advantages of high specific strength and specific modulus, strong designability, capability of integral forming and the like, and has wide application in the fields of aerospace, rail transit, wind power generation and the like. At present, the molding technology of composite materials is many, and the products prepared by adopting the prepreg-autoclave molding process have few defects and good process stability, so that the molding process is most widely applied in the field of aviation.
The integral molding technology of the composite material comprises co-curing and co-cementing. Co-curing refers to a process in which two or more parts are formed into an integral part by one-time curing. Co-bonding refers to a process in which one or more parts that have been cured to shape and another one or more parts that have not been cured are cured and bonded into one piece in one cure by means of an adhesive, typically a glue film.
Some composite parts need to be integrally cured to meet the requirements of strength and light weight, and if co-bonding, secondary bonding or mechanical connection technology is adopted, the requirements of both strength and strengthening are difficult to meet.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a trapezoid framework structure of a carbon fiber composite material and a forming method thereof.
The aim of the invention is realized by the following technical scheme:
a trapezoid framework structure of carbon fiber composite material mainly comprises a front beam and a rear beam; the front and the rear of the C-shaped front beam are connected to form a front beam, and the front and the rear of the C-shaped rear beam are connected to form a rear beam; the first rib, the second rib and the short side of the third rib of the rib box are simultaneously connected with the back of the C-shaped front beam and the front of the C-shaped back beam, and the fourth rib of the rib box is simultaneously connected with the thin end head of the front beam and the web surface of the back beam.
The first rib, the second rib, the third rib and the fourth rib of the rib box are simultaneously provided with reinforcing cloth at the connecting position for reinforcement.
The front beam is of an I-shaped structure.
The back beam is of an I-shaped structure.
The method is specifically characterized in that: the front and the rear of the C-shaped front beam are connected through a curing method to form a front beam, and the front and the rear of the C-shaped rear beam are connected through a curing method to form a rear beam;
the short sides of the first rib, the second rib and the third rib of the rib box are simultaneously connected with the back of the C-shaped front beam and the front of the C-shaped back beam through a curing method, the fourth rib of the rib box is simultaneously connected with the thin end head of the front beam and the web surface of the back beam through a curing method,
the co-curing and forming process for the trapezoid framework of the carbon fiber composite material adopts a form of 'block paving and combined curing', and specifically comprises the following steps:
and firstly, cleaning the surfaces of all used dies, then wiping a release agent on the surfaces of the metal dies and the combined surface, and paving polytetrafluoroethylene release cloth on the surfaces of the wood-plastic dies. After the completion, the die is combined for use;
step two, paving the front beam and the rear beam on a metal mold respectively, paving the front beam and the rear beam on a wood-plastic mold respectively, and repairing the contact area of the prefabricated body and the fourth rib according to a mold scribing after the paving is completed;
and thirdly, paving and sticking the first rib, the second rib and the third rib on a female die wood-plastic die, taking out the prefabricated body, paving and sticking the cut reinforcing cloth on the prefabricated body, and sleeving the reinforcing cloth on a silicon rubber male die together. The fourth rib is directly paved on the male die;
fourthly, combining the front beam with the front beam, and combining the rear beam with the front beam, wherein the concrete method comprises the steps of aligning the die scribing lines of the front beam and the rear beam, aligning the left edge and the right edge, pre-compacting, filling the R angle after combination with a twisted strip made of unidirectional prepreg tape to be smooth, and then sealing and pasting the combined surface with prepreg. The combination method of the front and rear beams is the same as above;
taking out the wood-plastic molds of the front beam and the rear beam, and combining the metal molds of the front beam and the rear beam with the bottom plate mold;
sixth, respectively placing the first rib, the second rib, the third rib and the fourth rib male die in place; fastening a positioning stop block and 4 rib box male die molds to fit by using bolts;
and seventh, paving the cut reinforcing cloth at the vertical angle positions of the 4 rib boxes, which are contacted with the front beam and the rear beam.
And eighth step, placing the silicon rubber aluminum core soft mold pressurizing molds at the back of the front beam and the front of the back beam in place, and closing the upper cover plate mold.
And ninth, sealing the whole vacuum bag, and entering an autoclave for curing and forming.
The invention has the advantages that: the carbon fiber composite material trapezoid framework co-curing molding process is simple to operate and good in repeatability, and meanwhile the accuracy of the position of the rib box is effectively ensured; and the number of fasteners and the cementing procedure are reduced, the integrated molding from the structural design to the manufacture of the composite material is realized, the weight of the trapezoid framework is further reduced, and the production efficiency is improved.
Drawings
FIG. 1 is a schematic diagram of a trapezoid framework structure of a carbon fiber composite material;
FIG. 2 is a schematic diagram of a silicon rubber aluminum core soft mold structure;
FIG. 3-1 is a schematic diagram of a reinforcement fabric paving;
FIG. 3-2 is a schematic diagram of a reinforcement fabric lay-up.
The marks in the drawings are: 1-a front beam; 2-front beam front; 3-the rear of the front beam; 4-a rear beam; 5-front of the rear beam; 6-rear beam; 7-a first rib; 8-a second rib; 9-a third rib; 10-fourth ribs; 11-silicone rubber soft film; 12-an aluminum core; 13-reinforcing cloth.
Detailed Description
The present invention will be described in further detail below. The rib box and the front and rear beams of the carbon fiber composite material component are co-cured and integrally molded, so that the adhesive joint interface effect between the rib box and the front and rear beams in the traditional secondary adhesive joint molding is solved, the weight of the trapezoid framework is reduced, and the product quality is improved.
Example 1
A trapezoid framework structure of carbon fiber composite material mainly comprises a front beam 1 and a rear beam 4; the front 2 of the C-shaped front beam and the rear 3 of the C-shaped front beam are connected to form a front beam, and the front 5 of the C-shaped rear beam and the rear 6 of the C-shaped rear beam are connected to form a rear beam; the short sides of the first rib 7, the second rib 8 and the third rib 9 of the rib box are simultaneously connected with the back of the C-shaped front beam and the front of the C-shaped back beam, and the fourth rib 10 of the rib box is simultaneously connected with the thin end head of the front beam and the web surface of the back beam.
The first rib, the second rib, the third rib and the fourth rib of the rib box are simultaneously provided with reinforcing cloth at the connecting position for reinforcement.
The co-curing and forming process of the trapezoid framework of the carbon fiber composite material comprises the following steps of:
and in the first step, cleaning the surfaces of all used moulds, then wiping the surfaces and the combined surfaces of the front beam front and back beams, the first rib male mould, the second rib male mould, the third rib male mould, the fourth rib male mould and the metal mould of the silicon rubber aluminum core 12 for at least 2 times, and paving polytetrafluoroethylene demolding cloth on the surfaces of the front beam rear and back beams, the first rib female mould, the second rib female mould and the third rib female mould. After the front beam and the rear beam are finished, the front beam and the rear beam are combined and used;
secondly, paving 3-4 layers of carbon fiber fabric prepreg on the front beam front and rear beam rear metal molds respectively, paving 3-4 layers of carbon fiber fabric prepreg on the front beam rear and rear beam front wood-plastic molds respectively, vacuumizing and compacting after the paving is finished, and repairing the contact area of the prefabricated body and the fourth rib according to the mold score line;
and thirdly, paving 4 layers of carbon fiber fabric prepreg on the first rib, the second rib and the third rib female die wood-plastic die, vacuumizing and compacting, taking out the prefabricated body, paving the cut 40mm reinforcing cloth on the prefabricated body, and sleeving the reinforcing cloth on the silicon rubber male die together. Directly paving 4 layers of carbon fiber fabric prepreg on the fourth rib silicon rubber aluminum core male die, vacuumizing and compacting;
fourthly, combining the front beam with the front beam, and combining the rear beam with the front beam, wherein the concrete method comprises the steps of aligning the die scribing lines on the front beam and the rear beam, aligning the left edge and the right edge, vacuumizing and compacting, filling the R angle after combination with a twisted strip made of unidirectional prepreg tape, and then sealing and pasting the combined surface with 1 layer of carbon fiber fabric prepreg. The combination method of the front and rear beams is the same as above;
taking out the wood-plastic molds of the front beam and the rear beam, and combining the metal molds of the front beam and the rear beam with the bottom plate mold;
sixth, respectively placing the first rib, the second rib, the third rib and the fourth rib male die in place; fastening a positioning stop block and 4 rib box male die molds to fit by using bolts;
and seventh, paving the cut 40mm reinforcing cloth at the vertical angle positions of the 4 rib boxes, which are contacted with the front beam and the rear beam.
And eighth step, placing the silicon rubber aluminum core soft mold 11 compression molds at the front beam back and the back beam front in place, and closing the upper cover plate mold.
And ninth, sealing the integral vacuum bag, establishing a vacuum system, checking the vacuum degree, wherein the vacuum degree is required to be below-85 KPa, the vacuum leakage is not more than 17KPa within 5min, and then the vacuum bag enters an autoclave for curing and forming.
The foregoing is merely a preferred embodiment of the present invention, and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the concept of the present invention, and are intended to be within the scope of the present invention.
Claims (4)
1. The co-curing and forming method for the trapezoid framework of the carbon fiber composite material is characterized by adopting a form of 'block paving and combined curing', and specifically comprises the following steps:
firstly, cleaning the surfaces of all used dies, then wiping a release agent on the surfaces of the metal dies and the combined surface, and paving polytetrafluoroethylene release cloth on the surfaces of the wood-plastic dies; after the completion, the die is combined for use;
step two, paving the front beam and the rear beam on a metal mold respectively, paving the front beam and the rear beam on a wood-plastic mold respectively, and repairing the contact area of the prefabricated body and the fourth rib according to a mold scribing after the paving is completed;
thirdly, paving and sticking the first rib, the second rib and the third rib on a female die wood-plastic die to be solid, taking out the prefabricated body, paving and sticking the cut reinforcing cloth on the prefabricated body, and sleeving the reinforcing cloth on a silicon rubber male die together; the fourth rib is directly paved on the male die;
fourthly, combining the front beam with the front beam, and combining the rear beam with the front beam, wherein the concrete method comprises the steps of aligning the die scribing lines of the front beam and the rear beam, aligning the left edge and the right edge, pre-compacting, filling the R angle after combination with a twisted strip made of unidirectional prepreg tape to be smooth, and then sealing and pasting the combined surface with prepreg; the combination method of the front and rear beams is the same as above;
taking out the wood-plastic molds of the front beam and the rear beam, and combining the metal molds of the front beam and the rear beam with the bottom plate mold;
sixth, respectively placing the first rib, the second rib, the third rib and the fourth rib male die in place; fastening a positioning stop block and 4 rib box male die molds to fit by using bolts;
seventh, paving the cut reinforcing cloth at the vertical angle positions of the 4 rib boxes, which are contacted with the front beam and the rear beam;
eighth, placing the silicon rubber aluminum core soft mold pressurizing molds at the back of the front beam and the front of the back beam in place, and closing the upper cover plate mold;
ninth, sealing the whole vacuum bag, and entering an autoclave for curing and forming;
the carbon fiber composite material trapezoid framework structure mainly comprises a front beam and a rear beam; the front and the rear of the C-shaped front beam are connected to form a front beam, and the front and the rear of the C-shaped rear beam are connected to form a rear beam; the first rib, the second rib and the short side of the third rib of the rib box are simultaneously connected with the back of the C-shaped front beam and the front of the C-shaped back beam, and the fourth rib of the rib box is simultaneously connected with the thin end head of the front beam and the web surface of the back beam.
2. The co-curing molding method of a carbon fiber composite trapezoidal skeleton according to claim 1, wherein the first rib, the second rib, the third rib and the fourth rib of the rib box are simultaneously provided with reinforcing cloth at the connection position.
3. The co-curing molding method of the trapezoid framework of the carbon fiber composite material is characterized in that the front part of the C-shaped front beam and the rear part of the C-shaped front beam are connected through a curing method to form a front beam, and the front part of the C-shaped rear beam and the rear part of the C-shaped rear beam are connected through a curing method to form a rear beam.
4. The co-curing molding method of the trapezoid framework of the carbon fiber composite material according to claim 1, wherein the short sides of the first rib, the second rib and the third rib of the rib box are simultaneously connected with the back of the front beam of the 'C' -shaped front beam and the front of the back beam of the 'C' -shaped rear beam by a curing method, and the fourth rib of the rib box is simultaneously connected with the thin end head of the front beam and the web surface of the back beam by the curing method.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810609725.9A CN108688195B (en) | 2018-06-13 | 2018-06-13 | Trapezoidal skeleton structure of carbon fiber composite material and forming method thereof |
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| CN201810609725.9A CN108688195B (en) | 2018-06-13 | 2018-06-13 | Trapezoidal skeleton structure of carbon fiber composite material and forming method thereof |
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| CN108688195B true CN108688195B (en) | 2024-04-09 |
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Families Citing this family (4)
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| CN110216901B (en) * | 2019-07-11 | 2024-01-26 | 沈阳西子航空产业有限公司 | Curing and forming device and method for composite material box and tube combined type closed cavity part |
| CN114919210A (en) * | 2022-04-22 | 2022-08-19 | 南京聚隆复合材料技术有限公司 | Forming method of composite material wing framework |
| CN115042453B (en) * | 2022-06-22 | 2024-03-08 | 沈阳飞机工业（集团）有限公司 | Thin-wall tool for manufacturing H-shaped variable-section honeycomb sandwich structure composite material part |
| CN117162539B (en) * | 2023-11-02 | 2024-02-06 | 成都泰格尔航天航空科技股份有限公司 | Compacting device and production process thereof |
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| CN108688195A (en) | 2018-10-23 |
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