CN108262984A - A kind of fabric composite material structural member and preparation method thereof - Google Patents
A kind of fabric composite material structural member and preparation method thereof Download PDFInfo
- Publication number
- CN108262984A CN108262984A CN201710104737.1A CN201710104737A CN108262984A CN 108262984 A CN108262984 A CN 108262984A CN 201710104737 A CN201710104737 A CN 201710104737A CN 108262984 A CN108262984 A CN 108262984A
- Authority
- CN
- China
- Prior art keywords
- structural member
- composite material
- support
- tube wall
- fabric composite
- 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.)
- Withdrawn
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 183
- 239000004744 fabric Substances 0.000 title claims abstract description 147
- 238000002360 preparation method Methods 0.000 title claims description 13
- 239000000463 material Substances 0.000 claims abstract description 53
- 239000000835 fiber Substances 0.000 claims abstract description 46
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 29
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 29
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 14
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 14
- 238000010276 construction Methods 0.000 claims abstract description 14
- 230000015572 biosynthetic process Effects 0.000 claims abstract description 5
- 238000003475 lamination Methods 0.000 claims description 54
- 238000004804 winding Methods 0.000 claims description 45
- 238000005452 bending Methods 0.000 claims description 20
- 230000005540 biological transmission Effects 0.000 claims description 8
- 239000011248 coating agent Substances 0.000 claims description 6
- 238000000576 coating method Methods 0.000 claims description 6
- 239000000203 mixture Substances 0.000 claims description 6
- 239000002023 wood Substances 0.000 claims description 6
- 238000009958 sewing Methods 0.000 claims description 4
- 238000009833 condensation Methods 0.000 claims description 3
- 230000005494 condensation Effects 0.000 claims description 3
- 239000003356 suture material Substances 0.000 claims description 3
- 150000001875 compounds Chemical class 0.000 claims description 2
- 125000004122 cyclic group Chemical group 0.000 claims description 2
- 238000011049 filling Methods 0.000 claims description 2
- 230000001413 cellular effect Effects 0.000 abstract description 8
- 239000007787 solid Substances 0.000 abstract description 3
- 239000004917 carbon fiber Substances 0.000 description 22
- 238000010586 diagram Methods 0.000 description 12
- 239000004033 plastic Substances 0.000 description 11
- 229920003023 plastic Polymers 0.000 description 11
- 239000000853 adhesive Substances 0.000 description 9
- 230000001070 adhesive effect Effects 0.000 description 9
- 239000006260 foam Substances 0.000 description 9
- 230000005855 radiation Effects 0.000 description 6
- 239000002184 metal Substances 0.000 description 4
- 229910052751 metal Inorganic materials 0.000 description 4
- 125000006841 cyclic skeleton Chemical group 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 229920006248 expandable polystyrene Polymers 0.000 description 3
- 238000005187 foaming Methods 0.000 description 3
- 238000003780 insertion Methods 0.000 description 3
- 230000037431 insertion Effects 0.000 description 3
- 239000007769 metal material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 239000004411 aluminium Substances 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 238000007664 blowing Methods 0.000 description 2
- 238000005253 cladding Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 229910001338 liquidmetal Inorganic materials 0.000 description 2
- DMKSVUSAATWOCU-HROMYWEYSA-N loteprednol etabonate Chemical compound C1CC2=CC(=O)C=C[C@]2(C)[C@@H]2[C@@H]1[C@@H]1CC[C@@](C(=O)OCCl)(OC(=O)OCC)[C@@]1(C)C[C@@H]2O DMKSVUSAATWOCU-HROMYWEYSA-N 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- OAICVXFJPJFONN-UHFFFAOYSA-N Phosphorus Chemical compound [P] OAICVXFJPJFONN-UHFFFAOYSA-N 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 210000000988 bone and bone Anatomy 0.000 description 1
- 238000009954 braiding Methods 0.000 description 1
- 239000003575 carbonaceous material Substances 0.000 description 1
- 238000003763 carbonization Methods 0.000 description 1
- 210000003850 cellular structure Anatomy 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 239000004567 concrete Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000002788 crimping Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 210000003746 feather Anatomy 0.000 description 1
- 239000002657 fibrous material Substances 0.000 description 1
- 238000002309 gasification Methods 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 229910052698 phosphorus Inorganic materials 0.000 description 1
- 239000011574 phosphorus Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000012779 reinforcing material Substances 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 239000004616 structural foam Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 230000004580 weight loss Effects 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
-
- 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
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
-
- 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
- B29L2023/00—Tubular articles
- B29L2023/22—Tubes or pipes, i.e. rigid
-
- 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
- B29L2031/60—Multitubular or multicompartmented articles, e.g. honeycomb
- B29L2031/601—Multi-tubular articles, i.e. composed of a plurality of tubes
- B29L2031/602—Multi-tubular articles, i.e. composed of a plurality of tubes composed of several elementary tubular elements
-
- 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
- B29L2031/60—Multitubular or multicompartmented articles, e.g. honeycomb
- B29L2031/608—Honeycomb structures
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a kind of fabric composite material structural member, the outer formation tubulose of the structural member, the tubular structural member is the fabric composite material honeycomb duct of fabric composite material support.The tubular structural member of honeycomb support is made in fabric composite material by the present invention, it can make prepared structural member in stress, the power born is distributed in cellular each branch, it is uniformly distributed on structural member, enhance the stress degree of structural member entirety, common carbon fibre composite can bear very strong pressure, but the ability for being subject to pressure is poor, the pipe inner support of structural member is supported using cellular carbon fabric composite material, structural member can be made to bear pressure to a certain extent, increase the field of load and Impact direction of structural member.The present invention is cellular by supports, reduces material and weight compared with solid construction part, has saved cost, while have stronger stress-bearing capability compared to hollow structural component.
Description
Technical field
The present invention relates to fabric composite material applied technical fields, and in particular to a kind of fabric composite material knot
Component and preparation method thereof.
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,
Carbon fibre composite proceeds by use in many fields.
Under the overall situation of global energy-saving and emission-reduction, automotive light weight technology increasingly becomes trend, plastics, composite material etc. in automobile
On application it is more and more extensive, existing metal structure is substituted using fibrous composite, is to realize to reduce automobile exhaust pollution
And reach energy-efficient effective way.Carbon fiber is the fibrous carbon material that a kind of phosphorus content is more than 90 percent, is had very high
Intensity and elasticity modulus, carbon fibre composite can pass through matrix, the selection of fiber, carbon fiber content and the optimization of distribution
Design, makes the various high-performance components that disclosure satisfy that multiple fields requirement.
On orthodox car, for transporting passenger, remaining is all moved only centesimal gasoline in itself for automobile, is used
Fibrous composite replaces steel, vehicle weight can be made to mitigate more than half, and weight loss effect is lighter than metal material by 50 percent,
It is lighter than aluminium by 30 percent, in addition, fibrous composite as automobile component have high-strength light, designability it is good, zero
Part integration, impact resistance is good, corrosion resistance and good, it is easily molded the advantages that.Fibrous composite is in automotive brake pads, wheel at present
It is applied on the parts such as hub, the also less appearance of the application in automobile overall skeleton.
Invention content
In view of the above-mentioned problems, the object of the present invention is to provide a kind of fabric composite woods available for vehicle complete vehicle skeleton
Expect structural member and preparation method thereof.
To achieve the above object, the present invention adopts the following technical scheme that：
A kind of fabric composite material structural member, the outer formation tubulose of the structural member, the tubular structural member are fabric
The fabric composite material honeycomb duct of composite material support；Fabric composite material therein has straight burr braiding and twill to compile
It knits.
Sandwich material either fibrous composite pipe or sky are filled in the honeycomb hole of the composite material honeycomb duct
Heart support element.
The fibrous braid composite material honeycomb duct of the fabric composite material support refers to and is folded by what suture sutured
Layer fabric composite material, using suture as the radial support of support shaft, forms starlike support construction.
The fabric composite material support, refers to the stratified fiber Fabric composites sutured by suture, and part is folded
Layer fabric composite material winding forms the winding pipe support using suture for the radial connection of support shaft into winding pipe,
The stratified fiber Fabric composites that another part is sutured by suture using suture as the radial support of support shaft, is formed
Radiation and winding pipe composite support.
The fabric composite material honeycomb duct of the fabric composite material support, refers to the lamination sutured by suture
Fabric composite material, respectively winding form the winding pipe branch using suture as the radial connection of support shaft into winding pipe
Support.
The fabric composite material honeycomb duct of the fabric composite material support, refers to the lamination sutured by suture
Fabric composite material is one group of lamination, wherein N >=2 per N layers, after radial one section of the stretching of each group of lamination, every group
Lamination, which is separated, to be stretched out to form N number of branch to N number of direction, after each branch overlaps two-by-two with the branch of other groups of laminations respectively and is stretched
Go out to form edge to support for radial honeycomb；Or winding pipe, the fiber are sutured in the honeycomb hole of honeycomb support
The fabric composite material honeycomb duct of Fabric composites support, refers to the stratified fiber fabric composite wood sutured by suture
Material, is one group of lamination per N layer, wherein N >=2, and into winding pipe, remaining layering is radial for partial hierarchical winding in every group of lamination
It is separated after stretching out one section, stretching forms multiple branches, after each branch overlaps two-by-two with the branch of other groups of laminations respectively and stretches
Go out to form edge to support for radial honeycomb.
The section of the honeycomb duct forms multi-layer honeycomb hole, outermost layer is tube wall outward centered on axle center.
The fabric composite material by support shaft to tube wall outside, then along tube wall bending, be bonded with tube wall
A part for tube wall, makes complete tube wall and fabric composite material that its internal backing material passes through along tube wall bending is whole
Body connects.
After the fabric composite material is by support shaft to tube wall, continues to stretch out tube wall, externally connect as structural member
The component connect enables the stress of external connection component to be transferred to backing material.
The fabric composite material by support shaft to tube wall outside, then along tube wall bending, form one of tube wall
Point, with the backing material stretch out tube wall again jointly after bending to the backing material for stretching out tube wall, make external connection component by
Power can be transferred to tube wall and the backing material of Qi Nei.
The quantity of the tube wall inner support axis is at least 2, is connected and supported by fabric composite material between support shaft.
Outer contour shape difference or outer contour shape of the structural member along the cross section of the different parts of the axis of pipe
It is identical but of different sizes.
The tubular structural member is branch-like, for " Y " alphabetical branch-like, " T " letter branch-like or " ten " word branch-like, and institute
Stating tubular structural member supervisor, not only tube wall is connect, and the support shaft in pipe also connects with branched pipe.
The structural member forms whole space frame structure.
The entirety space frame structure, it in the honeycomb hole of starlike support in honeycomb duct is cyclic annular sandwich material to be
Either fibrae circulares composite material tube or annular hollow support element, the fabric are carbon fibre fabric, form carbon fiber
Fabric composites overall skeleton.
The carbon fabric composite material overall skeleton, when the quantity of same cross section inner support axis is at least 2, branch
It is connected and supported by fabric composite material between support axis.
A kind of transmission shaft or support column prepared by the fabric composite material structural member.
A kind of preparation method of fabric composite material structural member, includes the following steps：
1）The graphics of structural member needed for drafting；
2）The die drawing of structural member core model is made according to graphics and makes structural member core model, which corresponds to honeycomb hole and set core model
Column, the core model are sandwich material either fibrous composite pipe or hollow strutting piece；
3）The die drawing of structural member external mold is made according to graphics and makes structural member external mold；
4）According to the spatial form of fabric composite material being each used to support in graphics structural member, determine that it is flat respectively
Face shape；
5）According to step 4）Flat shape, cut fabric material prepreg, equally, according to step 4）With 5）It determines
And cut tube wall prepreg；
6）The suture of prepreg is determined according to graphics；
7）By each prepreg according to the position of determining suture, by each prepreg lamination for needing lamination；
8）The prepreg of lamination according to the position of suture is sutured, manual suture or sewing machine suture can be used；
9）The lamination prepreg of suture is shaken apart, the honeycomb hole for forming prepreg according to graphics corresponds to the core model of core model
Core model column is inserted into corresponding honeycomb hole by column, and outside prepreg is coated on the outside of core model column；
10）Tube wall prepreg is coated core model to form tube wall again；
11）The core model for coating tube wall prepreg is filled in into external mold；
12）Core model is heated, cures and either external mold is heated, cure or is simultaneously heated core model and external mold, curing, later
Core model, external mold are taken out to get required structural member.
The step 9）Need to stretch out tube wall in middle outside prepreg as connector, prepreg reservation does not coat core
On the outside of mould column, remaining is coated on the outside of core model column.
The common stretching of support prepreg overlapping for needing the tube wall prepreg as connector with stretching out tube wall
Tube wall.
The prepreg of the common overlapping for stretching out tube wall is stitched together, and fills in the external mold of mutual cooperation, continues other
Step.
The step 2）In core model, by foam, foaming is prepared in a mold.
The tubular structural member of honeycomb support is made in fabric composite material by the present invention, can make prepared structure
Part is distributed in cellular each branch in stress, by the power born, and is uniformly distributed on structural member, enhances structural member
Whole stress degree, common carbon fibre composite can bear very strong pressure, but the ability for being subject to pressure is poor,
The pipe inner support of structural member using cellular carbon fabric composite material is supported, structural member can be made to a certain extent
Pressure is born, increases the field of load and Impact direction of structural member.The present invention is cellular by supports, compared with solid construction
Part reduces material and weight, has saved cost, while have stronger stress-bearing capability compared to hollow structural component.
Meanwhile the vehicle skeleton or airframe being prepared by the fabric composite material structural member of the present invention, with
Traditional vehicle or aircraft are compared, and have many advantages, such as that light weight, stress intensity are big, high temperature resistant, impact resistance are good.
Description of the drawings
Fig. 1 is structural representation Fig. 1 of radial support.
Fig. 2 is structural representation Fig. 2 of radial support.
Fig. 3 is structural representation Fig. 3 of radial support.
Fig. 4 is structural representation Fig. 4 of radial support.
Fig. 5 is radiation and structural representation Fig. 1 of winding pipe composite support.
Fig. 6 is radiation and structural representation Fig. 2 of winding pipe composite support.
Fig. 7 is the structure diagram of winding tubular support.
Fig. 8 is structural representation Fig. 1 of the radial support with mold.
Fig. 9 is structural representation Fig. 2 of the radial support with mold.
Figure 10 is the radiation with mold and the structure diagram of winding pipe composite support.
Figure 11 is the structure diagram of the winding tubular support with mold.
Figure 12 is structural representation Fig. 1 of body frame.
Figure 13 is structural representation Fig. 2 of body frame.
Figure 14 is the structure diagram of cyclic skeleton support.
Figure 15 is the enlarged diagram at A positions in Figure 13.
Figure 16 is fibrous composite joint structure schematic diagram 1.
Figure 17 is fibrous composite joint structure schematic diagram 2.
Figure 18 is structural representation Fig. 3 of body frame.
Figure 19 is structural representation Fig. 1 of hollow strip shape body supporting block.
Figure 20 is structural representation Fig. 2 of hollow strip shape body supporting block.
Figure 21 is the structure diagram of the honeycomb duct in multi-layer honeycomb hole.
Figure 22 is the structure diagram of the honeycomb duct of two starlike supports.
Figure 23 is the structure diagram of the honeycomb duct of three starlike supports.
Figure 24 is the enlarged structure schematic diagram of part B in Figure 12.
Specific embodiment
For those skilled in the art is made to more fully understand the present invention, the present invention is done With reference to embodiment
It further illustrates：
As shown in Figures 1 to 7, a kind of fabric composite material structural member, the outer formation tubulose of the structural member, the tubulose knot
Component is the fabric composite material honeycomb duct of fabric composite material support；Fabric composite material therein includes
Straight burr weaves and twill weave, and the fabric composite material is carbon fiber or glass fibre.
Sandwich material either fibrous composite pipe or sky are filled in the honeycomb hole of the composite material honeycomb duct
Heart support element.The sandwich material is mainly hard foam, can be rigid foam, Rigid structural foams material
Material mainly has PVC, PEI, PU, PET, PMI, AIREX, DIAB, 3A, STRUCELL, ROHACELL etc., also including rigid foam gold
Belong to material；The fibrous composite pipe can be carbon fiber woven composite pipe or carbon fiber winding composite material tube；
The hollow strutting piece, can be hollow plastic material thin-walled support element or hollow metal thin-walled support element, hollow plastic thin wall branch
Support member can be blowing part.
As shown in Figures 1 to 4, the fibrous braid composite material honeycomb duct of the fabric composite material support, refers to
The stratified fiber Fabric composites sutured by suture, using suture as the radial support of support shaft, forms starlike support
Structure, then starlike one layer of fabric composite material of support construction external sheath as tube wall, forms honeycomb duct, starlike branch again
The hole that support structure is formed is honeycomb hole, naturally it is also possible to which starlike support construction forms honeycomb hole with tube wall.
As shown in Figure 5 and Figure 6, the fabric composite material support refers to the stratified fiber fabric sutured by suture
Composite material, part stratified fiber Fabric composites winding are formed into winding pipe using suture as the radial company of support shaft
The winding pipe support connect, the stratified fiber Fabric composites that another part is sutured by suture are in by support shaft of suture
Radial support forms radiation and winding pipe composite support.Radial support or radiation can make with winding pipe composite support
Structural member is transferred to by the radial lamination branch being connect with tube wall in entire support in stress, by suffered power, can be with
Stress is made to be uniformly distributed on structural member, avoids structural member because force unbalance causes to deform or fractures；By support manufacturing into
It is radial that there is stronger endurance strength compared with hollow tube, while more solid tubing saves material, it is cost-effective.
As shown in fig. 7, the fabric composite material honeycomb duct of the fabric composite material support, refers to by suture
The stratified fiber Fabric composites of suture, respectively winding are formed into winding pipe using suture as the radial connection of support shaft
Winding pipe support 107, then in starlike one layer of fabric composite material of support construction external sheath as tube wall 207, structure
Into honeycomb duct；The tubing that winding pipe supports is used as transmission shaft or support column, can largely enhance transmission shaft or
The stress intensity of person's support column makes it be not easy flexural deformation or fracture.
As shown in figure 21, the fabric composite material honeycomb duct of the fabric composite material support, refers to by suturing
The stratified fiber Fabric composites that linear slit closes is one group of lamination per N layers, wherein N >=2, each group of radial stretching of lamination
After one section, every group of lamination, which is separated, to be stretched out to form N number of branch to N number of direction, each branch branch with other groups of laminations respectively
After overlapping two-by-two and composition edge is stretched out for the support of radial honeycomb；Or packet is sutured in the honeycomb hole of honeycomb support
Pipe crimping, the fabric composite material honeycomb duct of the fabric composite material support refer to the lamination fibre sutured by suture
Dimensional fabric composite material, is one group of lamination per N layer, wherein N >=2, in every group of lamination partial hierarchical winding into winding pipe, remaining
Be layered it is radial stretch out one section after separate, stretching forms multiple branches, each branch respectively with the branch of other groups of laminations two
After two overlappings and composition edge is stretched out for the support of radial honeycomb.As shown in figure 21, the section of the honeycomb duct using axle center as
Center, forms multi-layer honeycomb hole 16 outward, and outermost layer is tube wall 15.Honeycomb duct including multi-layer honeycomb hole 16 can be used as transmission
Axis or support column application, not only have the advantages that light weight, moreover, in 15 stress of tube wall, it can be by be forced through side
The radial branch of edge transmits, and makes the entire support that is distributed in of uniform force, this cellular support can be reduced accordingly
Tube wall stress, compared with the transmission shaft or support column of traditional structure, under identical stressing conditions, edge is fine for radial carbon
The tube wall of dimensional fabric composite material honeycomb support is not easy flexural deformation, extends the service life of transmission shaft or support column.
As shown in Figure 1, the fabric composite material is by support shaft to tube wall 201, then along 201 bending of tube wall,
A part for tube wall is bonded with tube wall, the backing material 101 for making complete tube wall internal with it passes through along tube wall bending
Fabric composite material is connected.Fabric composite material is extended into tube wall and along tube wall bending, it can be by tube wall
Institute's stress is reached in the fabric composite material support in pipe, so as to enhance the stress-bearing capability of tubing.
After the fabric composite material is by support shaft to tube wall, continues to stretch out tube wall, externally connect as structural member
The component connect enables the stress of external connection component to be transferred to backing material, makes backing material entirety stress, improves structure
The mechanical strength of part.As shown in Fig. 2, pipe inner support axis 102 is radial support, pipe inner support axis 102 has both ends to stretch out tube wall
202, the component 302 of two external connections is formed, shown in Fig. 6, pipe inner support axis 106 is radiation-winding pipe composite-like support,
Pipe inner support axis 106 has both ends to stretch out tube wall 206, forms the component 306 of two external connections；As shown in figure 3, pipe inner support axis
Tube wall 203 is stretched out in 103 one end, and the structural member of composition includes the component 303 of an external connection, shown in Fig. 5, pipe inner support axis
105 be radiation-winding pipe composite-like support, and 105 one end of pipe inner support axis stretches out tube wall 205, forms the portion of an external connection
Part 305.
As shown in figure 4, the fabric composite material extends to tube wall 204 by support shaft 104, then along tube wall 204
Bending forms a part for tube wall, stretches out tube wall again jointly with the backing material after bending to the backing material for stretching out tube wall,
The component 304 of structural member external connection is formed, the stress of external connection component can be enable to be transferred to tube wall and the support of Qi Nei
Material makes whole uniform force, so as to enhance the stress intensity of tubing.
The quantity of the tube wall inner support axis is at least 2, is connected and supported by fabric composite material between support shaft,
Multiple support shafts can preferably ensure the uniformity of stress, improve the stress intensity of structural member.
As shown in figure 22, the starlike support of the fabric composite material structural member can be 2, form honeycomb duct；
As shown in figure 23, the starlike support of the fabric composite material structural member can be 3, form honeycomb duct.Two in Figure 22
The honeycomb duct that a starlike support 17 is formed, tube wall 18 is forms after starlike 17 extension of support and bending.Three shape branch in Figure 23
The honeycomb duct structural member that support 19 is formed, tube wall 20 are formed by three starlike support, 19 bendings.
As needed, the structural member may be designed as the outer contour shape of the cross section of the different parts along the axis of pipe not
Together or outer contour shape is identical but of different sizes.
As shown in figure 15, separate in the honeycomb hole of the fabric composite material honeycomb duct 801 along support axis direction
Cross section setting support 802, the support on cross section can strengthen the stress intensity in axial direction, make structural member not variable in an axial direction
Shape or bending.
According to the needs of connecting component, the tubular structural member may be designed as branch-like, respectively " Y " alphabetical branch-like,
" T " letter branch-like or " ten " word branch-like, not only tube wall is connect the tubular structural member supervisor, and in pipe with branched pipe
Support shaft also connects, and referring to support shaft, either tube wall fabric is stitched together for continual entirety or fabric；If
Either then sandwich material is global formation or fibrous composite pipe to fibrous composite pipe to sandwich establishment structural material
It is that fabric is connected to be uninterrupted.The tube wall and starlike support of supervisor and branched pipe are mutually coupled respectively, it is ensured that supervisor
It is overall structure with branch's tube wall and starlike support, makes inside and outside stress consistent, avoid stress inside and outside structural member inconsistent and wrong
Position so cause to deform or damage.
The structural member forms whole space frame structure, refers to that structural member passes through " Y " alphabetical branch-like, " T " letter point
Branch shape or the connection of " ten " word branch-like, form whole space frame structure, such as form offroad vehicle skeleton, automotive framework, car
Skeleton, helicopter skeleton or passenger plane skeleton.
Especially the whole three-dimensional framework junction part is connect, and then assemble required vehicle skeleton by ring.Such as Figure 12
Vehicle skeleton 7 shown, that the ring connects, the starlike support in circumferential support used in ring termination process can merge, after merging
The support shaft of starlike support is linked together by carbon fabric composite material, and the tube wall of the starlike support after merging is also one
Whole tube wall；The vehicle skeleton 7 that the ring connects, the starlike support in circumferential support used in ring termination process can be separated, such as be schemed
The corner's part B for the vehicle skeleton that 12 middle rings connect, i.e., shown in Figure 24, between the support shaft of the starlike support in circumferential support
In separated position, so as to form " Y " alphabetical branch-like, " T " letter branch-like or " ten " word branch-like.
It is in separated position between the support shaft of starlike support in the circumferential support, so as to form " Y " alphabetical branch-like,
" T " letter branch-like or " ten " word branch-like, also are adapted for whole space frame structure；So the alphabetical branch-likes of " Y ",
" T " letter branch-like or " ten " word branch-like, branch as shown in Figure 24 or converge position, not only flat shape
" Y " letter branch-like, " T " alphabetical branch-like or " ten " word branch-like or flat shape is formed by bending this three-dimensional
A little shapes.
The structural member by grafting or ring is connect, may be constructed whole space frame structure, and then required for assembling
Overall skeleton.As shown in Figure 12 and Figure 13, the vehicle skeleton assembled for carbon fabric composite material.Figure 12 connects for ring
The vehicle skeleton 7 of gained is prepared, the circumferential support 9 used in ring termination process is as shown in figure 14, and the circumferential support 9 is knitted for fiber
Object composite material is heated, manufactured winding pipe or woven tube after curing；Figure 13 is vehicle skeleton 8 prepared by grafting, is such as schemed
Shown in 15, used 801 upper edge of structural member is axially arranged with support member 802 on vehicle skeleton 8, and support is set on structural member
The mechanical strength of vehicle can be further enhanced.
A kind of transmission shaft or support column prepared by above-mentioned fabric composite material structural member.
A kind of preparation method of fabric composite material structural member, includes the following steps：
1）The graphics of structural member needed for drafting；
2）The die drawing of structural member core model is made according to graphics and makes structural member core model, which corresponds to honeycomb hole and set core model
Column, the core model are sandwich material either fibrous composite pipe or hollow strutting piece；
3）The die drawing of structural member external mold is made according to graphics and makes structural member external mold；
4）According to the spatial form of fabric composite material being each used to support in graphics structural member, determine that it is flat respectively
Face shape；
5）According to step 4）Flat shape, cut fabric material prepreg, equally, according to step 4）With 5）It determines
And cut tube wall prepreg；
6）The suture of prepreg is determined according to graphics；
7）By each prepreg according to the position of determining suture, by each prepreg lamination for needing lamination；
8）The prepreg of lamination according to the position of suture is sutured, manual suture or sewing machine suture can be used；
9）The lamination prepreg of suture is shaken apart, the honeycomb hole for forming prepreg according to graphics corresponds to the core model of core model
Core model column is inserted into corresponding honeycomb hole by column, and outside prepreg is coated on the outside of core model column；
10）Tube wall prepreg is coated core model to form tube wall again；
11）The core model for coating tube wall prepreg is filled in into external mold；
12）Core model is heated, cures and either external mold is heated, is cured or simultaneously by core model and external mold heating, curing.
The step 9）Need to stretch out tube wall in middle outside prepreg as connector, prepreg reservation does not coat core
On the outside of mould column, remaining is coated on the outside of core model column.
The common stretching of support prepreg overlapping for needing the tube wall prepreg as connector with stretching out tube wall
Tube wall.
The prepreg of the common overlapping for stretching out tube wall is stitched together, fills in the external mold of mutual cooperation, continues it
Its step.
The step 2）Core mould, by foam in a mold foaming and be prepared.
It is as shown in Figs. 8 to 11, in the pipe walls support structural member preparation process for the present invention, partly comprising core model and external mold
Structural member schematic diagram.Shown in Fig. 8, core model 501 is inserted into using as the lamination prepreg 101 of support, then will stretch out core
The lamination bending of mould in outer layer covered fiber Fabric composites as tube wall 201, then answers the fabric for coating core model
Condensation material is inserted in external mold 601, is then heated, cures；Shown in Fig. 9, core is inserted into using as the lamination prepreg 102 of support
Part, is then stretched out the lamination bending of core model 502 by mould 502, and the lamination that tube wall 202 is stretched out in part stretches out conduct together with tube wall
Connecting component 302 in outer layer covered fiber Fabric composites as tube wall 202, then answers the fabric for coating core model
Condensation material is inserted in external mold 602, is then heated, cures；Shown in Figure 10, it is inserted into as the lamination prepreg 105 of support
Then the lamination winding of core model 505 is stretched out into winding pipe in part by core model 505, the lamination of tube wall 205 and tube wall one are stretched out in part
It rises and stretches out as connecting component 305, in outer layer covered fiber Fabric composites as tube wall 205, then will coat core model
Fabric composite material is inserted in external mold 605, is then heated, cures；It, will be as the lamination prepreg of support shown in Figure 11
Piece 107 is inserted into core model 507, then by the lamination winding of stretching core model 507 into winding pipe, in outer layer covered fiber fabric composite wood
Then the fabric composite material for coating core model 507 is inserted in the external mold 607 of corresponding structure, then by material as tube wall 207
It is heated, cures.
As shown in figure 18, the vehicle skeleton is by fabric composite material structural member and fabric composite joint
Grafting assembles；As shown in FIG. 16 and 17, the carbon fibre composite connector 10 is equipped with connection-peg 11, and connection-peg 11 is logical
Body is equipped with carbon fiber adhesive hair and hooks 12, and carbon fiber adhesive hair hooks 12 reversed dips to plugging direction；Connection-peg shown in Figure 16 is
The identical pipe of multiple outer diameters, the connection-peg shown in Figure 17 are the cellular pipe for being internally provided with multiple radial support plates.It inserts
Connector the whole body is equipped with carbon fiber adhesive hair and hooks, and carbon fiber adhesive hair hooks the reversed dip to plugging direction, and connection-peg can be smoothly inserted into
The insertion pipe of soft fibre adhesive hair is internally provided with, when negative direction is extracted, carbon fiber adhesive hair hook can catch on soft fibre adhesive hair, so as to
It prevents insertion pipe from coming off in connection-peg, is connected firmly, connection-peg and insertion pipe will not be damaged.
As illustrated in figures 19 and 20, the support that the grafting is assembled between the connection-peg of vehicle skeleton is hollow strip branch
Support, the hollow strip shape body supporting block of carbon fiber of Figure 19 are used for the support of straight line portion, the hollow strip shape body support of carbon fiber of Figure 20
Block supports for the transition of bending part, and the hollow strip shape body supporting block both ends of carbon fiber are enclosed construction, and center is hollow-core construction；
The hollow strip support is prepared by carbon fabric composite material.Under the premise of structural strength is ensured, material is saved
Material and weight, have saved cost.
The cyclic skeleton support ring that the vehicle skeleton is prepared by fabric composite material connects, the cyclic skeleton
The structural member of support is the fabric composite material structural member that pipe inner support is starlike support construction.The circumferential support ring connects
The vehicle skeleton formed, each ring are the honeycomb cellular structure member composition for being internally provided with multiple support constructions, ensure that vehicle bone
The mechanical strength of frame.
Ring connects the preparation method of vehicle skeleton being prepared, and includes the following steps：
1）The graphics of structural member needed for drafting；
2）The support construction figure of vehicle skeleton is drawn according to graphics and makes skeletal support, which is used to support fabric
Prepreg, the support are winding pipe or woven tube；
3）According to the spatial form of fabric composite material being each used to support in graphics structural member, determine that it is flat respectively
Face shape；
4）According to step 3）Flat shape, cut fabric material prepreg；
5）The suture of prepreg is determined according to graphics；
6）By each prepreg according to the position of determining suture, by each prepreg lamination for needing lamination；
7）The prepreg of lamination according to the position of suture is sutured, manual suture or sewing machine suture can be used；
8）The lamination prepreg of suture is shaken apart, skeletal support is corresponded in the honeycomb hole that prepreg is formed according to graphics,
Prepreg is wrapped up in corresponding honeycomb hole, outside prepreg is coated on the outside of skeletal support；
9）Tube wall prepreg is coated skeletal support to form tube wall again；
10）The above-mentioned skeletal support for being coated with tube wall is stitched together, vehicle skeleton is made；
11）By the heating of above-mentioned vehicle skeleton, curing.
The step 8）Described in honeycomb hole is corresponded into skeletal support, refer to the lamination prepreg that will be shaken apart according to three-dimensional
Empty cavity position in graph structure is put into skeletal support, then sutures the lamination prepreg of cladding in intersection, by skeleton branch
In support cladding cavity, play the role of supporting lamination prepreg.
The preparation method of carbon fibre composite connector that is hooked equipped with carbon fiber adhesive hair is：
（1）Organic fiber is become into the fiber of resistance to flame by stabilization processing, makes fiber not molten non-ignitable under high temperature cabonization, after
Fiber condition is held in continuation of insurance, then carries out roasting carbonization under high temperature in an inert atmosphere, organic fiber is made to lose part carbon and its
His non-carbon, forms with carbon fibrous material as main component i.e. carbon fiber；
（2）A water-soluble plastic pipe is taken, inclined hole is opened up on the plastic tube whole body；
（3）Carbon fiber is implanted in the inclined hole of plastic tube by feather planting machine；
（4）The external mold on set outside plastic tube；
（5）Foamed polystyrene pattern is added between external mold and plastic tube；
（6）Water-soluble plastic pipe is dissolved in water, is inserted into core model；
（7）Cylindrical cavity is formed between core model and foamed polystyrene pattern, alloy in lightweight is poured into a mould into cylindrical cavity, in liquid metals
Heat effect under, foamed polystyrene pattern occur pyrolytic gasification；
（8）After liquid metals cooling and solidifying, core model is taken out, forms the connection-peg hooked with carbon fiber adhesive hair.
Filling sandwich material or fibrous composite pipe in the honeycomb hole of above-mentioned all composite material honeycomb ducts
Or hollow strutting piece.The sandwich material is mainly hard foam, can be rigid foam, hard structure
Foamed material mainly has PVC, PEI, PU, PET, PMI, AIREX, DIAB, 3A, STRUCELL, ROHACELL etc., also including hard
Foam metal material；The fibrous composite pipe can be that carbon fiber woven composite pipe or carbon fiber winding are compound
Tubes of material；The hollow strutting piece, can be hollow plastic material thin-walled support element or hollow metal thin-walled support element, hollow plastics
Thin-walled support element can be blowing part.
Above-mentioned hard foam can be to be injected into honeycomb hole through foaming and intumescing so as to support bee socket bore wall.
Claims (21)
1. a kind of fabric composite material structural member, the outer formation tubulose of the structural member, it is characterised in that：The tubular structure
Part is the fabric composite material honeycomb duct of fabric composite material support.
2. fabric composite material structural member according to claim 1, it is characterised in that：The composite material honeycomb duct
Honeycomb hole in filling sandwich material either fibrous composite pipe or hollow strutting piece.
3. the fabric composite material structural member according to one of claims 1 or 2, it is characterised in that：The fiber
The fibrous braid composite material honeycomb duct of Fabric composites support, refers to the stratified fiber fabric composite wood sutured by suture
Material, using suture as the radial support construction of support shaft, forms starlike support construction.
4. the fabric composite material structural member described in one of claims 1 or 2, it is characterised in that：The fabric
Composite material support refers to the stratified fiber Fabric composites sutured by suture, part stratified fiber Fabric composites packet
Winding pipe is rolled into, the winding pipe using suture as the radial connection of support shaft is formed and supports, another part is sutured by suture
Stratified fiber Fabric composites, using suture as the radial support of support shaft, form it is starlike support it is compound with winding pipe
Support construction.
5. the fabric composite material structural member according to one of claims 1 or 2, it is characterised in that：The fiber
The fabric composite material honeycomb duct of Fabric composites support, refers to the stratified fiber fabric composite wood sutured by suture
Material, respectively winding form the winding pipe using suture as the radial connection of support shaft and support into winding pipe.
6. fabric composite material structural member according to claim 1, it is characterised in that：The fabric composite wood
Expect the fabric composite material honeycomb duct of support, refer to the stratified fiber Fabric composites sutured by suture, be one per N layers
Group lamination, wherein N >=2, after radial one section of the stretching of each group of lamination, every group of lamination is separated to be stretched out to form N to N number of direction
A branch after each branch overlaps two-by-two with the branch of other groups of laminations respectively and stretches out composition edge for radial honeycomb branch
Support；Or winding pipe, the fabric of the fabric composite material support are sutured in the honeycomb hole of honeycomb support
Composite material honeycomb duct refers to the stratified fiber Fabric composites sutured by suture, is one group of lamination per N layers, wherein N >=2,
Partial hierarchical winding separates, stretching forms multiple into winding pipe after radial one section of the stretching of remaining layering in every group of lamination
Branch after each branch overlaps two-by-two with the branch of other groups of laminations respectively and stretches out composition edge for radial honeycomb branch
Support.
7. the fabric composite material structural member according to one of claims 1 or 2, it is characterised in that：The honeycomb
The section of pipe forms multi-layer honeycomb hole, outermost layer is tube wall outward centered on axle center.
8. according to the fabric composite material structural member described in one of claim 3 or 4, it is characterised in that：The fiber
Fabric composites by support shaft to tube wall outside, then along tube wall bending, a part for tube wall is bonded with tube wall, has been made
The homogeneous tube wall backing material internal with it is connected by the fabric composite material along tube wall bending.
9. according to the fabric composite material structural member described in one of claim 3 or 4, it is characterised in that：The fiber
After Fabric composites is by support shaft to tube wall, continues to stretch out tube wall, as the component of structural member external connection, make externally to connect
The stress of relay part can be transferred to backing material.
10. according to the fabric composite material structural member described in claim 3 or 4, it is characterised in that：The fabric
Composite material by support shaft to tube wall outside, then along tube wall bending, a part for tube wall is formed, when bending is to stretching out tube wall
Tube wall is stretched out again jointly with the backing material, the stress of external connection component is enable to be transferred to tube wall and Qi Nei after backing material
Backing material.
11. the fabric composite material structural member according to one of claim 8-10, it is characterised in that：In the tube wall
The quantity of support shaft is at least 2, is connected and supported by fabric composite material between support shaft.
12. fabric composite material structural member according to claim 11, it is characterised in that：The structural member is along pipe
The outer contour shape of the cross section of the different parts of axis is different or outer contour shape is identical but of different sizes.
13. the fabric composite material structural member according to one of claim 11-12, it is characterised in that：The tubulose
Structural member is branch-like, is " Y " alphabetical branch-like, and " T " letter branch-like or " ten " word branch-like, the tubular structural member are responsible for
Not only tube wall is connect with branched pipe, and the support shaft in pipe also connects.
14. fabric composite material structural member according to claim 13, it is characterised in that：The structural member forms whole
Body space frame structure.
15. fabric composite material structural member according to claim 14, it is characterised in that：The entirety space framework
Structure, be in the honeycomb hole of starlike support in honeycomb duct cyclic annular sandwich material or fibrae circulares composite material tube or
Person's annular hollow support element, the fabric are carbon fibre fabric, form carbon fabric composite material overall skeleton.
16. fabric composite material structural member according to claim 15, it is characterised in that：The carbon fibre fabric is answered
Condensation material overall skeleton, when the quantity of same cross section inner support axis is at least 2, by fabric composite wood between support shaft
Material connection support.
17. transmission shaft or support column prepared by the fabric composite material structural member according to one of claim 5-7.
18. according to the preparation method of claim 1-16 any one of them fabric composite material structural members, feature exists
In：Include the following steps：
1）The graphics of structural member needed for drafting；
2）The die drawing of structural member core model is made according to graphics and makes structural member core model, which corresponds to honeycomb hole and set core model
Column, the core model are sandwich material either fibrous composite pipe or hollow strutting piece；
3）The die drawing of structural member external mold is made according to graphics and makes structural member external mold；
4）According to the spatial form of fabric composite material being each used to support in graphics structural member, determine that it is flat respectively
Face shape；
5）According to step 4）Flat shape, cut fabric material prepreg, equally, according to step 4）With 5）It determines
And cut tube wall prepreg；
6）The suture of prepreg is determined according to graphics；
7）By each prepreg according to the position of determining suture, by each prepreg lamination for needing lamination；
8）The prepreg of lamination according to the position of suture is sutured, manual suture or sewing machine suture can be used；
9）The lamination prepreg of suture is shaken apart, the honeycomb hole for forming prepreg according to graphics corresponds to the core model of core model
Core model column is inserted into corresponding honeycomb hole by column, and outside prepreg is coated on the outside of core model column；
10）Tube wall prepreg is coated core model to form tube wall again；
11）The core model for coating tube wall prepreg is filled in into external mold；
12）Core model is heated, cures and either external mold is heated, cure or is simultaneously heated core model and external mold, curing, later
Core model, external mold are taken out to get required structural member.
19. the preparation method of fabric composite material structural member according to claim 17, it is characterised in that：The step
Rapid 9）Needing to stretch out tube wall in middle outside prepreg as connector, prepreg reservation is not coated on the outside of core model column, remaining
It is coated on the outside of core model column.
20. the preparation method of fabric composite material structural member according to claim 18, it is characterised in that：The need
Tube wall is stretched out jointly with stretching out the support prepreg overlapping of tube wall as the tube wall prepreg of connector.
21. the preparation method of fabric composite material structural member according to claim 18, it is characterised in that：It stretches jointly
The prepreg for going out the overlapping of tube wall is stitched together, and fills in the external mold of mutual cooperation, continues other steps.
Priority Applications (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210427601.5A CN116968339A (en) | 2016-12-31 | 2017-02-24 | Fiber fabric composite structural member and preparation method thereof |
| PCT/CN2017/120419 WO2018121789A1 (en) | 2016-12-31 | 2017-12-31 | Fibre fabric composite structural component, automobile framework prepared using same, and method |
| JP2019536154A JP7378782B2 (en) | 2016-12-31 | 2017-12-31 | Fiber woven composite material structural member, automobile frame manufactured therefrom, and manufacturing method |
| JP2022089970A JP7364274B2 (en) | 2016-12-31 | 2022-06-01 | Fiber woven composite material structural member, automobile frame manufactured therefrom, and manufacturing method |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2016112687095 | 2016-12-31 | ||
| CN201611268709 | 2016-12-31 |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210427601.5A Division CN116968339A (en) | 2016-12-31 | 2017-02-24 | Fiber fabric composite structural member and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108262984A true CN108262984A (en) | 2018-07-10 |
Family
ID=62770783
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710104737.1A Withdrawn CN108262984A (en) | 2016-12-31 | 2017-02-24 | A kind of fabric composite material structural member and preparation method thereof |
| CN202210427601.5A Pending CN116968339A (en) | 2016-12-31 | 2017-02-24 | Fiber fabric composite structural member and preparation method thereof |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210427601.5A Pending CN116968339A (en) | 2016-12-31 | 2017-02-24 | Fiber fabric composite structural member and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN108262984A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109483902A (en) * | 2018-11-19 | 2019-03-19 | 东莞泰合复合材料有限公司 | A kind of carbon fiber product and application |
| CN109488097A (en) * | 2018-11-08 | 2019-03-19 | 中国电建集团河南电力器材有限公司 | A kind of carbon fabric composite material electric pole |
| CN109537975A (en) * | 2018-11-08 | 2019-03-29 | 郭东鑫 | A kind of telecommunications launching tower |
| CN113733596A (en) * | 2021-08-30 | 2021-12-03 | 北京航空航天大学 | Composite material light undercarriage wheel structure and forming method thereof |
| CN113910642A (en) * | 2021-09-28 | 2022-01-11 | 常州市新创智能科技有限公司 | Forming method and forming die for repairing bolt |
| WO2022247654A1 (en) * | 2021-05-24 | 2022-12-01 | 中联重科股份有限公司 | Fiber composite beam structure and manufacturing method therefor, boom section, boom, and mechanical device |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3742985A (en) * | 1967-01-31 | 1973-07-03 | Chemstress Ind Inc | Reinforced pipe |
| JPH07329196A (en) * | 1994-06-06 | 1995-12-19 | Bridgestone Sports Co Ltd | Synthetic resin tube reinforced by fiber |
| CN102006994A (en) * | 2008-04-15 | 2011-04-06 | 空中客车运作有限责任公司 | Method for manufacturing a core composite provided with cover layers on both sides as well as a core composite |
| CN103375677A (en) * | 2012-04-23 | 2013-10-30 | 通用汽车环球科技运作有限责任公司 | Magnesium-composite structures with enhanced design |
| CN103407171A (en) * | 2013-07-30 | 2013-11-27 | 北京航空航天大学 | Integral forming method for sewing enhanced cross connector made of fiber reinforced resin matrix composite |
| CN104039535A (en) * | 2011-12-07 | 2014-09-10 | 蒂森克虏伯碳素零件有限公司 | Wheel comprising a wheel spider, and suitable production method |
| US20140301859A1 (en) * | 2011-12-16 | 2014-10-09 | Vestas Wind Systems A/S | Wind turbine blades |
| CN104520094A (en) * | 2012-08-07 | 2015-04-15 | 埃尔塞乐公司 | Composite strap for connection between two parts |
| CN105014984A (en) * | 2015-06-09 | 2015-11-04 | 福建福联精编有限公司 | Three-dimensional warp-knitted spacer fabric impact-resistant composite material and manufacturing method and application thereof |
| JP2016125378A (en) * | 2014-12-26 | 2016-07-11 | トヨタ紡織株式会社 | Air intake duct and manufacturing method of air intake duct |
| CN105946246A (en) * | 2016-05-10 | 2016-09-21 | 河北科技大学 | Preparation method for carbon fiber honeycomb core materials |
-
2017
- 2017-02-24 CN CN201710104737.1A patent/CN108262984A/en not_active Withdrawn
- 2017-02-24 CN CN202210427601.5A patent/CN116968339A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3742985A (en) * | 1967-01-31 | 1973-07-03 | Chemstress Ind Inc | Reinforced pipe |
| JPH07329196A (en) * | 1994-06-06 | 1995-12-19 | Bridgestone Sports Co Ltd | Synthetic resin tube reinforced by fiber |
| CN102006994A (en) * | 2008-04-15 | 2011-04-06 | 空中客车运作有限责任公司 | Method for manufacturing a core composite provided with cover layers on both sides as well as a core composite |
| CN104039535A (en) * | 2011-12-07 | 2014-09-10 | 蒂森克虏伯碳素零件有限公司 | Wheel comprising a wheel spider, and suitable production method |
| US20140301859A1 (en) * | 2011-12-16 | 2014-10-09 | Vestas Wind Systems A/S | Wind turbine blades |
| CN103375677A (en) * | 2012-04-23 | 2013-10-30 | 通用汽车环球科技运作有限责任公司 | Magnesium-composite structures with enhanced design |
| CN104520094A (en) * | 2012-08-07 | 2015-04-15 | 埃尔塞乐公司 | Composite strap for connection between two parts |
| CN103407171A (en) * | 2013-07-30 | 2013-11-27 | 北京航空航天大学 | Integral forming method for sewing enhanced cross connector made of fiber reinforced resin matrix composite |
| JP2016125378A (en) * | 2014-12-26 | 2016-07-11 | トヨタ紡織株式会社 | Air intake duct and manufacturing method of air intake duct |
| CN105014984A (en) * | 2015-06-09 | 2015-11-04 | 福建福联精编有限公司 | Three-dimensional warp-knitted spacer fabric impact-resistant composite material and manufacturing method and application thereof |
| CN105946246A (en) * | 2016-05-10 | 2016-09-21 | 河北科技大学 | Preparation method for carbon fiber honeycomb core materials |
Non-Patent Citations (1)
| Title |
|---|
| 陈文亮: "《飞行器制造技术基础》", 30 April 2014, 北京航空航天大学出版社 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109488097A (en) * | 2018-11-08 | 2019-03-19 | 中国电建集团河南电力器材有限公司 | A kind of carbon fabric composite material electric pole |
| CN109537975A (en) * | 2018-11-08 | 2019-03-29 | 郭东鑫 | A kind of telecommunications launching tower |
| CN109483902A (en) * | 2018-11-19 | 2019-03-19 | 东莞泰合复合材料有限公司 | A kind of carbon fiber product and application |
| WO2022247654A1 (en) * | 2021-05-24 | 2022-12-01 | 中联重科股份有限公司 | Fiber composite beam structure and manufacturing method therefor, boom section, boom, and mechanical device |
| CN113733596A (en) * | 2021-08-30 | 2021-12-03 | 北京航空航天大学 | Composite material light undercarriage wheel structure and forming method thereof |
| CN113733596B (en) * | 2021-08-30 | 2022-08-19 | 北京航空航天大学 | Composite material light undercarriage wheel structure and forming mode thereof |
| CN113910642A (en) * | 2021-09-28 | 2022-01-11 | 常州市新创智能科技有限公司 | Forming method and forming die for repairing bolt |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116968339A (en) | 2023-10-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108262984A (en) | A kind of fabric composite material structural member and preparation method thereof | |
| US8101035B2 (en) | Composite mandrel | |
| CN103318203B (en) | With the Lightweight composite-material carriage structure of the aerodynamic force aerotrain of imitative wing | |
| CN102648080B (en) | Woven preform, composite, and method of making thereof | |
| CN103895717B (en) | Fibre reinforced plastics body construction and its manufacturing method | |
| CN105121175A (en) | Face to rim connection for a composite wheel | |
| DE102011111744B4 (en) | Control box module and manufacturing process | |
| US10300668B2 (en) | Composite structure and methods of assembling same | |
| JP5460821B2 (en) | Applicable blade | |
| US10464267B2 (en) | Continuous fiber lattice for reinforcing polymeric composites | |
| CN112936912B (en) | Composite material transmission shaft and forming method thereof | |
| CN112622308B (en) | Carbon fiber composite material arm section and preparation method thereof | |
| JP2011522723A (en) | Method for manufacturing structural parts made from organic matrix composites and the resulting parts | |
| CN108263496A (en) | Carbon fabric composite material vehicle skeleton and preparation method thereof | |
| WO1996009159A1 (en) | Method of making internally reinforced composite tubes | |
| CN108263497A (en) | Carbon fabric composite material vehicle skeleton and preparation method thereof | |
| GB2564963A (en) | Method for producing a bearing bush, bearing bush and control arm for a wheel suspension of a motor vehicle | |
| CN111409312A (en) | High-torsion-resistance carbon fiber woven pultrusion composite material pipe and preparation method thereof | |
| WO2018121789A1 (en) | Fibre fabric composite structural component, automobile framework prepared using same, and method | |
| US6793183B1 (en) | Integral node tubular spaceframe | |
| CN108262983A (en) | Carbon fabric composite material vehicle skeleton and preparation method thereof | |
| JPH03161326A (en) | Pipe fitted with flange made of fiber reinforced composite material and preparation thereof | |
| JP7364274B2 (en) | Fiber woven composite material structural member, automobile frame manufactured therefrom, and manufacturing method | |
| CN106142594A (en) | For producing the equipment and method strengthening structure | |
| CN108608794A (en) | Composite material wheel hub and preparation method thereof |
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 | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20200909 Address after: 222-19, room 1356, No. 450000 East navigation road, Zhengzhou economic and Technological Development Zone, Henan, China Applicant after: Henan Kyrgyzstan patent operating Co. Address before: 2 C7-2 building, No. 55, Holly Road, Zhengzhou hi tech Industrial Development Zone, Henan 450000, China Applicant before: ZHENGZHOU JITIAN PATENT OPERATION Co.,Ltd. |
|
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20180710 |