CN109866912A - A kind of composite fibre window frame for aircraft and its forming method - Google Patents
A kind of composite fibre window frame for aircraft and its forming method Download PDFInfo
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- CN109866912A CN109866912A CN201910222292.6A CN201910222292A CN109866912A CN 109866912 A CN109866912 A CN 109866912A CN 201910222292 A CN201910222292 A CN 201910222292A CN 109866912 A CN109866912 A CN 109866912A
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- 239000000835 fiber Substances 0.000 title claims abstract description 54
- 238000000034 method Methods 0.000 title claims abstract description 26
- 239000002131 composite material Substances 0.000 title claims abstract description 14
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 14
- 239000004917 carbon fiber Substances 0.000 claims abstract description 14
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 14
- 238000009826 distribution Methods 0.000 claims abstract description 6
- 239000011347 resin Substances 0.000 claims abstract description 6
- 229920005989 resin Polymers 0.000 claims abstract description 6
- 238000007711 solidification Methods 0.000 claims abstract description 3
- 230000008023 solidification Effects 0.000 claims abstract description 3
- 239000010410 layer Substances 0.000 claims description 67
- 238000009954 braiding Methods 0.000 claims description 43
- 239000002356 single layer Substances 0.000 claims description 10
- 239000011229 interlayer Substances 0.000 claims description 8
- 238000009941 weaving Methods 0.000 claims description 8
- 238000009958 sewing Methods 0.000 claims description 7
- 125000004122 cyclic group Chemical group 0.000 claims description 6
- 239000004744 fabric Substances 0.000 claims description 6
- 238000009940 knitting Methods 0.000 claims description 4
- 238000004026 adhesive bonding Methods 0.000 claims description 2
- 230000015572 biosynthetic process Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 3
- 238000000465 moulding Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000004513 sizing Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 235000013527 bean curd Nutrition 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000003028 elevating effect Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
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- Woven Fabrics (AREA)
Abstract
The invention discloses a kind of composite fibre window frame for aircraft and its forming methods, carbon fiber wire is wound on window frame 3D bolster model by braider, successively knit out multiple fibrous layers, each fibrous layer can predetermined angle of weave, different angles is woven by different Impact directions, realizes the prefabricated body formed of window frame；Through multi-layer braided arrival thickness, Impact direction being coped with by the strike angle of different layers fiber, then prefabricated component is formed, size needed for meeting subsequent resin solidification requires and the distribution of the continuity of all single fibers makes product stress intensity reach maximum requirement.The present invention optimizes stress by multi-layer braided different machine direction, reduces the artificial laying of conventional needs and laying overlaps the bad problem of effect.
Description
Technical field
The invention belongs to composite molding field, in particular to a kind of composite fibre window frame for aircraft and its forming method.
Background technique
Composite material has excellent mechanical property and light-weighted clear superiority, has in aircraft aerospace obvious
Advantage, be widely used in aircraft manufacturing or even rocket, guided missile etc..If Boeing 787,350 dosage of Air Passenger are more than 50%, and
Chinese big Aircraft Project 929 also will be used largely, for manufacturing fuselage, empennage, spar, elevating plane, the machine Door and window frame of aircraft
Deng.
Open market uses scrim cloth, builds up laying by different angle direction classes, and such as 0 degree, -45 degree, 45 degree, 90 degree
Deng；Or the method using carbon fiber bundle sewing, by different requirements, cyclic annular single layer sewing, certain function shape is sewed
Different single layers, then multilayer build-up.However these methods are for planar member or small curvature part or local surface that there is no problem,
But for certain three-dimensional shape, there is the stereochemical structure on cap edge, there is difficult point.Even if using laying loss in certain feature
It has difficulties, proposes a such issues that method solves thus.
In order to be best understood from window frame for aircraft design feature, it is illustrated by taking Fig. 1 as an example.
As shown in Figure 1, window frame for aircraft has outward flange 1, inward flange 2 and perpendicular to vertical between above-mentioned two flange
Flange 3, section l-shaped turning, wherein at least one flange can be connected with aircaft configuration, and shown frame material is by compound fibre
Dimension molding increases resin by fiber and is solidified, and the window frame is made of multi-layer fiber layer, and the fibrous layer has independent or multiple
The machine direction of conjunction forms, and the fibrous layer machine direction is arranged along loading direction, by the above method come window frame for aircraft power
Specific strength, specific stiffness and fatigue behaviour.
Summary of the invention
The object of the present invention is to provide a kind of composite fibre window frame for aircraft and its forming methods, and window frame is made to have high intensity,
Single layer fibre continuously and realizes the enhancing of all directions mechanics, meets the stress of window frame complex environment in general direction.
First technical solution of the invention is: a kind of composite fibre window frame for aircraft, it is characterised in that: the window frame includes compiling
Knit molding precast body, and by the cured reinforced resin of precast body；The precast body by the woven formation of multilayer fibrous layer group
At fibrous layer is made of single layer braiding, and for fiber at positive and negative angle of weave, fiber is knitted to form whole cyclic annular knot alternatively up and down in layer
Structure；The fiber of positive and negative angle of weave is made of the fiber of both direction, and is intact fibre from start and ending is woven.
Preferably, it can be woven by different angle of weave between different fibrous layers, meet fiber by loading direction
It is required that.
Preferably, pass through one or both of gluing and interlayer sewing mode between the multi-layer fiber layer of the precast body
To be formed.
Preferably, the precast body of the knitting forming includes inward flange and outward flange, and perpendicular to above-mentioned two flange
Vertical flanges, and one of flange is connected with aircaft configuration.
Second technical solution of the invention is: a kind of composite fibre window frame for aircraft forming method passes through carbon fiber wire
Braider is wound on window frame bolster model, successively knits out multiple fibrous layers, each fibrous layer can predetermined angle of weave, i.e.,
Different angles is woven by different Impact directions, realizes the prefabricated body formed of window frame；Through multi-layer braided arrival thickness, pass through
The strike angle of different layers fiber copes with Impact direction, and then prefabricated component is formed, ruler needed for meeting subsequent resin solidification
The distribution of the continuity of very little requirement and all single fibers makes product stress intensity reach maximum requirement.
Preferably, precast body is annular or ring-band shape multi-layer braided structures, and each single layer of rings ring band passes through braiding one
Molding, it is whole without disconnection, connection or closed state.
Preferably, carbon fiber wire trend, distribution are consistent during single layer braiding, and carbon fiber wire presses certain angle in braided fabric
It is mutually overlapping, and each silk is complete ribbon.
Preferably, the carbon fiber wire braiding wide-angle is ± 30 degree ~ ± 90 degree, realizes that axially loaded requires braiding；Carbon
It is ± 0 degree ~ ± 30 degree that fiber filament, which weaves low-angle, realizes circumferential force request braiding；Wide-angle braiding layer and low-angle braiding
Layer carries out alternately braiding.
Preferably, the precast body after the braiding is reinforced by 3D sewing sizing and interlayer.
Preferably, 3D braiding is carried out by braider on window frame bolster model, is cut from the small bore direction of window frame towards big
The braiding of face direction forms certain angle and overlaps two-by-two, realizes that single fiber forms braiding by certain angle of weave by control
Body, i.e., the braided fabric of two positive and negative angle of weave make angle of weave meet the requirement of Impact direction, realize maximum load capacity；?
Continue to weave on the basis of braiding first layer, form precast body after weaving multilayer, precast body is removed from window frame bolster model,
Precast body is formed by interlayer sewing, subsequent carry out curing process.
Due to being using multi-layer braided, fiber is successively split on entire workpiece head to tail portion fiber, the entire ring of window frame
Shape structure be also it is integral, ensure that whole cyclic annular stress condition, these situations are the not available spies of laying, shredded dried bean curd sewing
Property, monolithic stability is improved, and braiding process can be improved whole anisotropic situation by different layers different angle.
It is mutually to overlap due to the method using braiding, between fiber, the structure between fiber is stabilized between each fiber,
It realizes the continuity of fiber and plays the maximum intensity advantage of carbon fiber；Molding is continuously woven between layer keeps enough interlayer patches
It is closely knit between the advantages of conjunction and fiber that volume fraction can be improved, it realizes enough high-volume fractionals, higher performance requirement is provided.
Due to being replaced using the layer of different weaving directions, wide-angle braiding layer promotes Impact direction performance, this layer
Even if there is certain deformation to tend in loading process, effect of the broadwise layer by power is woven into axial twine due to broadwise layer
It is coiled into annular structure, deformation is limited and expands, it is new to be obtained higher stabilization by the latitudinal constraint of its outer coversheet.
It is intact fibre from braiding start and ending, single fiber is continuous and machine direction can be with when single layer weaves
The directional spreding of stress optimizes stress by multi-layer braided different machine direction, reduces the artificial laying of conventional needs and laying
The undesirable some problems of effect are overlapped, increase that fiber distribution is neat and fibre density is distributed almost the same advantage and can be real
The advantage now automated.
Detailed description of the invention
It is described in further detail below in conjunction with attached drawing and embodiments of the present invention
Fig. 1 is window frame structure schematic diagram；
Fig. 2 is window frame 3D bolster model figure；
Fig. 3 is window frame first layer 3 D weaving partial schematic diagram；
Fig. 4 is window frame second layer 3 D weaving partial schematic diagram；
Fig. 5 is window frame wide-angle layer and low-angle layer relation schematic diagram.
Specific embodiment
Referring to attached drawing.The composite fibre window frame for aircraft of the present embodiment is made of multi-layer braided molding fibrous layer, by weaving
Machine (Brainding Machine) carries out 3D braiding on the basis of window frame 3D bolster model, and braiding winds out multiple fibrous layers,
The 3D precast body of window frame is formed, the specific method is as follows:
It is as shown in Figure 2 that window frame 3D bolster model 4(is obtained according to window frame model analysis production), on the basis of 3D bolster model,
It is woven by braider from small end to big extreme direction, forms certain angle and overlap two-by-two, single fiber is realized by control
Knitted body is formed by certain helix angle, i.e., the braided fabric of two positive and negative helix angles (claiming angle of weave afterwards) makes braid angle
Degree meets the requirement of Impact direction, realizes maximum load capacity.
In order to realize the requirement of multi-direction bearing capacity, continue on the basis of weaving first layer weave the second layer, third layer,
4th layer ..., it is ± 30 degree ~ ± 90 degree that carbon fiber wire, which weaves wide-angle, realizes that axially loaded requires braiding；Carbon fiber wire is compiled
Knitting low-angle is ± 0 degree ~ ± 30 degree, realizes circumferential force request braiding；When practical braiding, wide-angle braiding layer and low-angle are compiled
Tissue layer carries out alternately braiding.Such as first layer 5 is first woven, by ± 60 degree (braiding situations of part as shown in Figure 3), complete first
After layer braiding, continue to weave the second layer 6 in original woven base, by ± 20 degree (braiding situations of part as shown in Figure 4), if
It is the bearing capacity for circumferential direction, helix angle can be minimized, realizes circumferential force request；So by wide-angle, small
Angle repeats braiding in layer and thickeies, and reaches Product Process and requires thickness, multi-layer braided is both for the need of multi-direction stress
It wants, also for the needs for reaching thickness of workpiece.
Due to using multilayered structure, as shown in figure 5, the independent 2 layers of structure of analysis, the braiding structure that internal layer 7 is ± 60 degree, outside
Layer 8 is ± 20 degree of braiding cyclic structures, when the forms situation that deforms is, if stress F as shown in the figure occurs for internal layer 7, to make
Fiber can be intended to straight line deformation, drive internal layer 7 to F1 Direction distortion, due to ± 20 degree of the cyclic structure ring by outer layer 8
Around the direction F1 is loaded into outer layer 8 and hinders 7 fibre deformation of internal layer, stablizes mechanism.
It after the completion of braiding, is formed certain size and fiber orientation requires prefabricated component, precast body is supported from window frame 3D
It removes on model, gets ready for technique processes such as subsequent cures.As needed, the braided part removed from support construction can
To be sewed using 3D, carries out prefabricated component sizing and interlayer is reinforced.
Claims (10)
1. a kind of composite fibre window frame for aircraft, it is characterised in that: the window frame includes the precast body of knitting forming, and precast body is consolidated
The reinforced resin of change；The precast body is made of the fibrous layer of the woven formation of multilayer, and fibrous layer is made of single layer braiding, in layer
Fiber is knitted to form whole cyclic structure at positive and negative angle of weave, fiber alternatively up and down；The fiber of positive and negative angle of weave is by two
The fiber in direction forms, and is intact fibre from start and ending is woven.
2. a kind of composite fibre window frame for aircraft as described in claim 1, it is characterised in that: can be by difference between different fibrous layers
Angle of weave woven, meet fiber by the requirement of loading direction.
3. a kind of composite fibre window frame for aircraft as described in claim 1, it is characterised in that: the multi-layer fiber layer of the precast body
Between mode one or both of sewed to be formed by gluing and interlayer.
4. a kind of composite fibre window frame for aircraft as described in claim 1, it is characterised in that: the precast body packet of the knitting forming
Include inward flange and outward flange, and perpendicular to the vertical flanges of above-mentioned two flange, and one of flange and aircaft configuration phase
Even.
5. carbon fiber wire is wound into window frame support by braider by a kind of forming method of window frame for aircraft described in claim 1
On model, successively knit out multiple fibrous layers, each fibrous layer can predetermined angle of weave, i.e., not by the braiding of different Impact directions
Same angle, realizes the prefabricated body formed of window frame；Through multi-layer braided arrival thickness, pass through the strike angle of different layers fiber
Impact direction is coped with, then prefabricated component is formed, size needed for meeting subsequent resin solidification requires and all single fibers
Continuity distribution makes product stress intensity reach maximum requirement.
6. forming method as claimed in claim 5, it is characterised in that: precast body is annular or ring-band shape multi-layer braided structures,
Each single layer of rings ring band is integrally formed by braiding, whole without disconnection, connection or closed state.
7. forming method as claimed in claim 5, it is characterised in that: carbon fiber wire trend, distribution one during single layer braiding
It causes, carbon fiber wire is mutually overlapping by certain angle in braided fabric, and each silk is complete ribbon.
8. forming method as claimed in claim 5, it is characterised in that: carbon fiber wire braiding wide-angle is ± 30 degree ~ ±
90 degree, realize that axially loaded requires braiding；It is ± 0 degree ~ ± 30 degree that carbon fiber wire, which weaves low-angle, realizes that circumferential force request is compiled
It knits；Wide-angle braiding layer and low-angle braiding layer carry out alternately braiding.
9. forming method as claimed in claim 5, it is characterised in that: the precast body after the braiding is sewed by 3D and is formed
Reinforce with interlayer.
10. forming method as claimed in claim 5, it is characterised in that: carry out 3D by braider on window frame bolster model
Braiding, weaves from the small bore direction of window frame towards big cross-wise direction, forms certain angle and overlaps two-by-two, is realized by control single
Fiber forms knitted body by certain angle of weave, i.e., the braided fabric of two positive and negative angle of weave makes angle of weave meet stress
Maximum load capacity is realized in the requirement in direction；Continue to weave on the basis of weaving first layer, form precast body after weaving multilayer,
Precast body is removed from window frame bolster model, precast body is formed by interlayer sewing, subsequent carry out curing process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910222292.6A CN109866912A (en) | 2019-03-22 | 2019-03-22 | A kind of composite fibre window frame for aircraft and its forming method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910222292.6A CN109866912A (en) | 2019-03-22 | 2019-03-22 | A kind of composite fibre window frame for aircraft and its forming method |
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| Publication Number | Publication Date |
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| CN109866912A true CN109866912A (en) | 2019-06-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910222292.6A Pending CN109866912A (en) | 2019-03-22 | 2019-03-22 | A kind of composite fibre window frame for aircraft and its forming method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110370683A (en) * | 2019-07-18 | 2019-10-25 | 上海大界机器人科技有限公司 | A kind of carbon fiber braiding apparatus and system |
| CN117416063A (en) * | 2023-12-19 | 2024-01-19 | 浙江航引新材料科技有限公司 | Composite material reinforcing rib preform and preparation method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005153680A (en) * | 2003-11-25 | 2005-06-16 | Shikibo Ltd | Dry preform for window frame made of frp used for aircraft |
| CN101249725A (en) * | 2007-02-23 | 2008-08-27 | 斯奈克玛 | Method of manufacturing a gas turbine casing out of composite material, and a casing as obtained thereby |
| EP1995046A2 (en) * | 2007-05-25 | 2008-11-26 | The Boeing Company | Method of fabricating fiber reinforced composite structure having stepped surface |
| CN105366073A (en) * | 2015-11-24 | 2016-03-02 | 江苏恒神股份有限公司 | Method for manufacturing fiber-laid and seamed window frame precast body |
| CN209757497U (en) * | 2019-03-22 | 2019-12-10 | 宁波慈星股份有限公司 | Composite fiber aircraft window frame |
-
2019
- 2019-03-22 CN CN201910222292.6A patent/CN109866912A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005153680A (en) * | 2003-11-25 | 2005-06-16 | Shikibo Ltd | Dry preform for window frame made of frp used for aircraft |
| CN101249725A (en) * | 2007-02-23 | 2008-08-27 | 斯奈克玛 | Method of manufacturing a gas turbine casing out of composite material, and a casing as obtained thereby |
| EP1995046A2 (en) * | 2007-05-25 | 2008-11-26 | The Boeing Company | Method of fabricating fiber reinforced composite structure having stepped surface |
| CN105366073A (en) * | 2015-11-24 | 2016-03-02 | 江苏恒神股份有限公司 | Method for manufacturing fiber-laid and seamed window frame precast body |
| CN209757497U (en) * | 2019-03-22 | 2019-12-10 | 宁波慈星股份有限公司 | Composite fiber aircraft window frame |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110370683A (en) * | 2019-07-18 | 2019-10-25 | 上海大界机器人科技有限公司 | A kind of carbon fiber braiding apparatus and system |
| CN117416063A (en) * | 2023-12-19 | 2024-01-19 | 浙江航引新材料科技有限公司 | Composite material reinforcing rib preform and preparation method thereof |
| CN117416063B (en) * | 2023-12-19 | 2024-03-05 | 浙江航引新材料科技有限公司 | Composite material reinforcing rib preform and preparation method thereof |
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Application publication date: 20190611 |