CN108262998A - The method that the carbon fiber winding composite material structural member of riveting prepares space framework - Google Patents
The method that the carbon fiber winding composite material structural member of riveting prepares space framework Download PDFInfo
- Publication number
- CN108262998A CN108262998A CN201710138610.1A CN201710138610A CN108262998A CN 108262998 A CN108262998 A CN 108262998A CN 201710138610 A CN201710138610 A CN 201710138610A CN 108262998 A CN108262998 A CN 108262998A
- Authority
- CN
- China
- Prior art keywords
- composite material
- ring
- shaped frame
- liner
- space framework
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
-
- 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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
-
- 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
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The present invention relates to the methods that a kind of carbon fiber winding composite material structural member of riveting prepares space framework, the carbon fiber winding composite material structural member is cellular composite material tube prepared by continuous carbon fibre, the honeycomb hole of cellular composite material tube is continuous carbon fibre wound composite pipe, at least two compositions are whole a branch of, adjacent winding pipe contact with each other position by rivet together, so as to which adjacent winding pipe be made to link together, whole cellular composite material tube is formed.Using the space framework light weight of this method preparation, rigidity is high, safety is good, can be as the skeleton of automobile, car and seat.
Description
Technical field
The present invention relates to the methods that a kind of carbon fiber winding composite material structural member of riveting prepares space framework.
Background technology
With the fast development of modern technologies, higher requirement is proposed to material, carbon fiber has high intensity, resistance to height
Warm, corrosion-resistant, endurance, light weight can bear the characteristic that very big pulling force etc. is significantly higher than steel, aluminium etc., belong to typical height
Performance fibers have overwhelming advantage relative to traditional metal material.Carbon fiber is removed alone as adiabatic heat-insulation material
Material is outer, is added in the materials such as resin, metal, ceramics, concrete usually as reinforcing material, forms carbon fibre composite.
The composite material force structure and preparation method of reasonable design are needed when carbon fibre composite is used as structural member, can just be filled
Carbon fiber is waved in distribution can bear very big this advantage of pulling force.
Invention content
Carbon fiber maximum feature is can to bear very big pulling force in carbon fibre composite, and resin bears pressure, existing
Material is made inner tubular portion and does not support, and if plate is made, since plate thickness is too small, generation torque is small, does not make full use of carbon
Fiber can bear the advantages of very big pulling force, so needing to study how to give full play to the side that carbon fiber bears this advantage of pulling force
Method.It needs the carbon fibre composite light product of density is made thus, if foam is made, since continuous fiber can not
Foaming, that is, allow to foam, and the performance of resin can be had an impact after foaming, original performance is lost, can not bear very big drawing
Power, therefore how to realize carbon fibre composite as structural member and become to bear very big pulling force for very big problem.
The present invention is exactly to provide a kind of carbon fiber winding composite material structural member preparation of riveting to solve the above-mentioned problems
The method of space framework.
The present invention uses following technical scheme：A kind of carbon fiber winding composite material structural member of riveting prepares space framework
Method, the carbon fiber winding composite material structural member be continuous carbon fibre prepare cellular composite material tube, it is cellular
The honeycomb hole of composite material tube is continuous carbon fibre wound composite pipe, and at least two form whole a branch of, adjacent winding
Pipe contact with each other position by rivet together, so as to which adjacent winding pipe be made to link together, form whole honeycomb
Shape composite material tube, the method for preparing space framework include the following steps：
（1）Draw the space framework three-dimensional drawing；
（2）Rubber liner is made according to each ring-shaped frame shape of space framework respectively, rubber liner is disconnected for a side
Ring-shaped frame, both ends wherein one end of disconnection are closed, and the other end is set into outlet passageway, and the position that liner disconnects is longer than ring-shaped frame
2.5cm；
（3）External mold is made according to each ring-shaped frame shape respectively；
（4）Selection matches diameter and the preimpregnation carbon fiber winding composite material tube of length with rubber liner；
（5）Composite material tube is respectively fitted on liner；
（6）It will be sleeved in the corresponding external mold of prepreg composite materials pipe merging of liner, then locked mode；
（7）It is charged and discharged gas repeatedly to liner, makes to generate slightly play between winding fiber, make wound composite honeycomb cellular structure member
It is suitble to the shape of winding lines；
（8）Cure preimpregnation wound composite honeycomb cellular structure member to liner pressurized, heated；
（9）The ring-shaped frame that all one side disconnect is made respectively；
（10）Each ring-shaped frame is combined with each other together；
（11）The ring-shaped frame grafting of each disconnection is closed.
The step（10）In, it is adjacent as a branch of ring-shaped frame contact with each other position by rivet together.
Carbon fiber can bear very big pulling force, and will not deform, but be made as it is solid if, not only can waste of materials, increase
Add weight, and performance raising is also little, therefore the present invention is designed according to the thickness and stress of pipe, so as to be optimal hair
It waves carbon fiber and bears very big this performance of pulling force；Using the space framework light weight of this method preparation, rigidity is high, safety is good,
It can be as the skeleton of automobile, car and seat.
Description of the drawings
Fig. 1 is the structure diagram of carbon fiber winding composite material structural member.
Fig. 2 is carbon fiber winding composite material tube structure diagram.
Fig. 3 is adjacent winding pipe attachment structure schematic diagram.
Fig. 4 is adjacent winding pipe connection procedure schematic diagram 1.
Fig. 5 is adjacent winding pipe connection procedure schematic diagram 2.
Fig. 6 is the structure diagram of space framework.
Specific embodiment
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings.
As shown in Figure 1, Figure 2, shown in Fig. 3 and Fig. 6, a kind of carbon fiber winding composite material structural member of riveting prepares space framework
Method, the carbon fiber winding composite material structural member be continuous carbon fibre prepare cellular composite material tube, it is cellular
The honeycomb hole of composite material tube is continuous carbon fibre wound composite pipe 1, and at least two form whole a branch of, fiber winding side
As the winding method of steel wire in high pressure steel wire sebific duct, the adjacent winding pipe position that contacts with each other is riveted on method by rivet 2
Together, so as to which adjacent winding pipe be made to link together, whole cellular composite material tube is formed, prepares the side of space framework
Method includes the following steps：
（1）Draw the space framework three-dimensional drawing；
（2）Rubber liner is made according to each ring-shaped frame shape of space framework respectively, rubber liner is disconnected for a side
Ring-shaped frame, both ends wherein one end of disconnection are closed, and the other end is set into outlet passageway, and the position that liner disconnects is longer than ring-shaped frame
2.5cm；
（3）External mold is made according to each ring-shaped frame shape respectively；
（4）Selection matches diameter and the preimpregnation carbon fiber winding composite material tube of length with rubber liner；
（5）Composite material tube is respectively fitted on liner；
（6）It will be sleeved in the corresponding external mold of prepreg composite materials pipe merging of liner, then locked mode；
（7）It is charged and discharged gas repeatedly to liner, makes to generate slightly play between winding fiber, make wound composite honeycomb cellular structure member
It is suitble to the shape of winding lines, eliminates fibre stress；
（8）Cure preimpregnation wound composite honeycomb cellular structure member to liner pressurized, heated；
（9）The ring-shaped frame that all one side disconnect is made respectively；
（10）Each ring-shaped frame is combined with each other together；
（11）The ring-shaped frame grafting of each disconnection is closed.
The step（10）In, it is adjacent as a branch of ring-shaped frame contact with each other position by rivet together.
As shown in Figure 4 and Figure 5, the method for adjacent wound composite pipe riveting is：Take a core pipe 3,3 both sides of core pipe
Groove 4 or multiple holes are respectively equipped with, core pipe 3 is inserted into prepreg composite materials pipe, in prepreg composite materials Guan Shangyu grooves 4 or hole
Rivet 2 is inserted into corresponding position, what rivet 2 was made for carbon fibre composite, is hard at room temperature, then take a core pipe 3,
Core pipe 3 is inserted into another composite material tube, this composite material tube and a upper composite material tube are put together, and make riveting
The other end of nail 2 is also inserted into this composite material tube, is then heated, and rotates two core pipes 3 respectively, and rivet 2 heats and softens, and two
A composite material tube is heating and curing, and so as to which adjacent composite material tube be riveted together, finally extracts two core pipes 3 out.
Claims (2)
1. the method that a kind of carbon fiber winding composite material structural member of riveting prepares space framework, it is characterised in that：The carbon
The cellular composite material tube that filament wound composite structural member is prepared for continuous carbon fibre, the bee of cellular composite material tube
Socket bore is continuous carbon fibre wound composite pipe, and at least two form whole a branch of, and adjacent winding pipe contacts with each other position
By rivet together, so as to which adjacent winding pipe be made to link together, whole cellular composite material tube is formed, is made
The method of standby space framework includes the following steps：
（1）Draw the space framework three-dimensional drawing；
（2）Rubber liner is made according to each ring-shaped frame shape of space framework respectively, rubber liner is disconnected for a side
Ring-shaped frame, both ends wherein one end of disconnection are closed, and the other end is set into outlet passageway, and the position that liner disconnects is longer than ring-shaped frame
2.5cm；
（3）External mold is made according to each ring-shaped frame shape respectively；
（4）Selection matches diameter and the preimpregnation carbon fiber winding composite material tube of length with rubber liner；
（5）Composite material tube is respectively fitted on liner；
（6）It will be sleeved in the corresponding external mold of prepreg composite materials pipe merging of liner, then locked mode；
（7）It is charged and discharged gas repeatedly to liner, makes to generate slightly play between winding fiber, make wound composite honeycomb cellular structure member
It is suitble to the shape of winding lines；
（8）Cure preimpregnation wound composite honeycomb cellular structure member to liner pressurized, heated；
（9）The ring-shaped frame that all one side disconnect is made respectively；
（10）Each ring-shaped frame is combined with each other together；
（11）The ring-shaped frame grafting of each disconnection is closed.
2. the method that the carbon fiber winding composite material structural member of riveting according to claim 1 prepares space framework,
It is characterized in that：The step（10）In, it is adjacent as a branch of ring-shaped frame contact with each other position by rivet together.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2016112671858 | 2016-12-31 | ||
| CN201611267185 | 2016-12-31 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108262998A true CN108262998A (en) | 2018-07-10 |
Family
ID=62770837
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710138610.1A Pending CN108262998A (en) | 2016-12-31 | 2017-03-09 | The method that the carbon fiber winding composite material structural member of riveting prepares space framework |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108262998A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86105307A (en) * | 1985-08-22 | 1987-04-01 | 布德公司 | Hollow fiber reinforced structure and preparation method thereof |
| WO1990002286A1 (en) * | 1988-08-22 | 1990-03-08 | Hex B-Group, Ltd. | Conduit liner assembly and method for installation |
| JPH07329196A (en) * | 1994-06-06 | 1995-12-19 | Bridgestone Sports Co Ltd | Synthetic resin tube reinforced by fiber |
| CN102431185A (en) * | 2011-09-20 | 2012-05-02 | 南京航空航天大学 | Curved surface self-adaptive pressure shoe and controlling method thereof |
-
2017
- 2017-03-09 CN CN201710138610.1A patent/CN108262998A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86105307A (en) * | 1985-08-22 | 1987-04-01 | 布德公司 | Hollow fiber reinforced structure and preparation method thereof |
| WO1990002286A1 (en) * | 1988-08-22 | 1990-03-08 | Hex B-Group, Ltd. | Conduit liner assembly and method for installation |
| JPH07329196A (en) * | 1994-06-06 | 1995-12-19 | Bridgestone Sports Co Ltd | Synthetic resin tube reinforced by fiber |
| CN102431185A (en) * | 2011-09-20 | 2012-05-02 | 南京航空航天大学 | Curved surface self-adaptive pressure shoe and controlling method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103889692B (en) | The internal tubulose strengthened is combined pole and manufacture method thereof | |
| CN105128876B (en) | A kind of carbon fibre composite car body and its manufacturing method | |
| CN101342942B (en) | Disposal solidifying and forming technique for frame and outer panel skin of wing profile | |
| CN106870924A (en) | The space framework and application of carbon fibre composite honeycomb cellular structure member and its preparation | |
| CN104552727A (en) | Preparation method of carbon fiber product | |
| CN107152603B (en) | Bistable shell structure and manufacturing method thereof | |
| CN104647771A (en) | K-cor foam sandwich enhanced composite material cap-shaped reinforcing rib wall plate structure and forming method thereof | |
| CN108262984A (en) | A kind of fabric composite material structural member and preparation method thereof | |
| CN104339668A (en) | Integrated forming method of carbon fiber chair backs | |
| CN105270599A (en) | Collapsible, coiled mandrel | |
| CN109897338A (en) | Polyether-ether-ketone composite material, housing of power cell and preparation method | |
| CN114030204A (en) | Non-autoclave molding method for large-size composite material barrel | |
| CN101837663B (en) | Locally-reinforced composite dot-matrix sandwich panel and preparation method thereof | |
| US20050056117A1 (en) | Composite strut and method of making same | |
| CN108262998A (en) | The method that the carbon fiber winding composite material structural member of riveting prepares space framework | |
| CN101890814B (en) | Preparation method of hollow round tube pyramid type completely composite material lattice laminboard | |
| CN108262978A (en) | The method that the carbon fiber winding composite material structural member of riveting prepares space framework | |
| CN108262977A (en) | The method that the carbon fiber woven composite materials and structures part of riveting prepares space framework | |
| JP2022520697A (en) | Methods for manufacturing girder beams for hollow composite structures, especially wind turbine rotor blades, and related mandrel | |
| CN108262997A (en) | The method that the carbon fiber woven composite materials and structures part of riveting prepares space framework | |
| JP2019502593A (en) | Process for producing bottom plate of equipment cabin in high-speed railway vehicle by composite material | |
| CN106828616A (en) | Slide fastener is engaged carbon fiber braiding structure part and ring connects space framework and the application of preparation | |
| CN108908950A (en) | A kind of carbon fiber pipe battle array structure and preparation method thereof | |
| CN102785371B (en) | Method for making composite material lattice sandwich boards by prepreg fiber bundles | |
| CN108263002A (en) | The method that slide fastener occlusion carbon fiber winding composite material structural member prepares space framework |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180710 |
|
| WD01 | Invention patent application deemed withdrawn after publication |