CN107962830B - A kind of method of carbon fiber structural layer of cloth cut-parts - Google Patents
A kind of method of carbon fiber structural layer of cloth cut-parts Download PDFInfo
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- CN107962830B CN107962830B CN201711359907.7A CN201711359907A CN107962830B CN 107962830 B CN107962830 B CN 107962830B CN 201711359907 A CN201711359907 A CN 201711359907A CN 107962830 B CN107962830 B CN 107962830B
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- blade
- curved surface
- parts
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- 239000004744 fabric Substances 0.000 title claims abstract description 41
- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 32
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 32
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 31
- 238000000034 method Methods 0.000 title claims abstract description 11
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 230000011218 segmentation Effects 0.000 claims description 4
- 239000003292 glue Substances 0.000 abstract description 6
- 239000000463 material Substances 0.000 abstract description 6
- 239000002131 composite material Substances 0.000 abstract description 5
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 238000013461 design Methods 0.000 abstract description 2
- 238000012797 qualification Methods 0.000 abstract description 2
- 239000010410 layer Substances 0.000 description 52
- 238000010586 diagram Methods 0.000 description 4
- 238000012360 testing method Methods 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 238000012669 compression test Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000002604 ultrasonography Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B1/00—Layered products having a non-planar shape
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2250/00—Layers arrangement
- B32B2250/20—All layers being fibrous or filamentary
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Treatment Of Fiber Materials (AREA)
- Laminated Bodies (AREA)
Abstract
The invention belongs to composite structure design fields, are related to a kind of method of carbon fiber structural layer of cloth cut-parts.The present invention is to spread process according to the forming principle and layer of blade, to solve because rear thickness is smaller, where biasing when overlay thickness, it may appear that surface intersection, where the layer of cloth of our requirements cannot be obtained the problem of curved surface.This cut-parts production method overcomes because that cannot obtain wanted laying curved surface, cuts cut-parts manually, improves the precision of cut-parts, it avoids expecting that perhaps few material causes blade richness glue or poor glue, causes leaf quality unstable because of layer of cloth cut-parts more, and product qualification rate is reduced, reduce production cost.
Description
Technical field
The invention belongs to composite structure design fields, are related to a kind of method of carbon fiber structural layer of cloth cut-parts.
Background technique
As national economic strength enhances, make great efforts the development to high-tech areas such as Aeronautics and Astronautics, develops all kinds of boats
It, aviation aircraft, need to carry out a large amount of wind tunnel test work, meanwhile, the resistance to compression heat resistanceheat resistants of a variety of materials test, automobile, height
Fast train, the air drag of ship, heat-resisting and compression test are also required to carry out wind tunnel test.Therefore low speed, transonic speed, ultrasound
Fast, hypersonic all types of wind-tunnel are rapidly developed, up to the present, China possessed low speed, high speed, ultrahigh speed and
The wind-tunnel such as shock wave, electric arc, for the variation to meet the market requirement, the product of my company will also do corresponding adjustment.
Compressor is the core equipment of continous way transonic wind tunnel, and compressor blade therein is key in core, is
The overall weight for reducing compressor, reduces the starting inertia of compressor, and composite material relies on its light weight, superior specific strength,
It is preferred as compressor blade that the advantages that specific stiffness, specific modulus and corrosion resistance, gradually replaces metal material.For reduce energy consumption,
Reduce compressor weight and rotary inertia, the main material using carbon fibre composite as compressor blade.To reduce energy
Consumption reduces compressor weight and rotary inertia, the foam using carbon fibre composite as the main material of compressor blade
Interlayer structure.Blade shifts to an earlier date blanking using prepreg, then carries out layer paving, finally by heating, compression molding.Under blade layer of cloth
Material, accurately cut-parts figure becomes very crucial.It when doing layer of cloth figure, is successively deviated, is deviated inwards since blade outer surface
With a thickness of ply gage.Then the curved surface offset out is unfolded by software.Trailing edge thickness is smaller, meeting when offset
There is surface intersection in rear, we are difficult to that curved surface is unfolded in this way, can only be because can not accomplish accurate blanking
Big a bit, when layer is spread pass through that layer of cloth cut-parts are done cuts complete layer paving manually.Cutting manually will appear uncertainty, and layer of cloth is excessive
Or very few the case where will appear poor glue and rich glue, less serious case influences presentation quality, serious to cause blade that use.
Summary of the invention
The purpose of the present invention: this patent is aimed to overcome that because spoon of blade cannot bias out the layer of cloth song that we want
Face can only make blade layer of cloth by cutting manually, lead to the problem that leaf quality is unstable.
A kind of technical solution of the present invention: method of carbon fiber structural layer of cloth cut-parts, which is characterized in that including following step
It is rapid:
1. uniformly choosing n plane on 1 axis of carbon fiber blade, n plane and carbon fiber blade 1 are made by software
Intersection curve, then by software solve intersection curve middle component curve；
2. spoon of blade 2 is divided in generation equally according to the middle component curve for the n intersection curve that step 1 is done；
3. extracting blade outer layer layer of cloth curved surface 3, ply gage is inwardly biased, blade outer layer layer of cloth curved surface curved face 4 is obtained；
4. dividing spoon of blade 2 equally in step 2, divides blade outer layer layer of cloth curved surface 4, remove extra curved surface, obtain
Required curved surface, required curved surface are unfolded to obtain required cut-parts figure by CATIA software.
Shown biasing ply gage: carbon fiber blade is made of n-layer layer of cloth, and ply gage is place n-th layer and first layer
Cloth interlamellar spacing.
Middle component curve: the normal direction straight line of peripheral curve top half is done, intersects two o'clock with peripheral curve, takes its midpoint simultaneously
Connection, obtains middle component curve.
Beneficial effects of the present invention: the present invention is the forming principle and process according to blade, to solve because of rear thickness ratio
It is smaller, where biasing when overlay thickness, it may appear that surface intersection cannot obtain the layer of cloth Surface Problems of our requirements.This sanction
Piece production method overcomes because that cannot obtain wanted laying curved surface, cuts cut-parts manually, improves the precision of cut-parts, avoid because of layer of cloth
Cut-parts expect that perhaps few material causes blade richness glue or poor glue, causes leaf quality unstable more, and reduce product qualification rate, drop
Low production cost.
Detailed description of the invention
Fig. 1 divides curved surface schematic diagram in being
Fig. 2 is offset surface schematic diagram
Fig. 3 be I at enlarged diagram,
The middle component curve schematic diagram of Fig. 4 intersection curve
In the figure 1-carbon fiber blade, 2-divide equally spoon of blade, I-trailing edge, 3- blade outer layer layer of cloth curved surface,
Layer of cloth curved surface after 4-offsets
Specific embodiment
As shown in Figure 1, a kind of method of carbon fiber structural layer of cloth cut-parts, comprising the following steps:
1. being ordered by catia software with " plane " and uniformly choosing n plane on 1 axis of carbon fiber blade, by soft
Part " intersection " order, is intersected to obtain n intersection curve with carbon fiber blade 1 with n plane, then by doing in curve normal orientation
In divide midpoint, with " spline curve " order connection midpoint, obtain the middle component curve of n intersection curve；
2. being divided equally according to the middle component curve in the n section that step 1 is done with the generation of catia software multi-section curve order
Spoon of blade 2；
3. extracting 1 outermost layer upper and lower surface blade outer layer layer of cloth curved surface 3 of carbon fiber blade respectively with order is extracted, it is biased inwardly
Ply gage is set, layer of cloth curved surface 4 after being deviated；
4. dividing spoon of blade 2 equally in step 2, layer of cloth curved surface 4 after segmentation offset removes extra curved surface, obtains institute
The Doubly curved surfaces are obtained required cut-parts figure by CATIA software by the curved surface needed.
Bias ply gage: carbon fiber blade 1 is made of n-layer layer of cloth, and ply gage is place n-th layer and first layer layer of cloth
Spacing.
Embodiment 1
Carbon fiber length of blade 900, carbon fiber trailing edge thickness is smaller than leading edge thickness, and carbon fiber trailing edge is minimum thick
Spend 3.125mm, maximum gauge 8.99mm.Carbon fiber blade practical ply gage 2.25mm, totally 18 layers, every thickness degree 0.125mm.
When carbon fiber blade does layer of cloth cut-parts, surface sheet body where layer of cloth need to be solved with CATIA software is general by deviating from carbon fiber
It ties up blade surface and extracts sheet body, obtain required sheet body, be then unfolded with expansion order, obtain required cut-parts.
Carbon fiber blade ply gage is 2.25mm, so the superposition at rear is greater than carbon fiber leaf with a thickness of 4.5mm
Piece rear minimum thickness 3.125mm, carbon fiber blade will appear intersection when biasing layer of cloth, be not directly available required piece
Body.Carbon fiber blade need to deviate 1.5 at the 12nd layer, and superposition thickness is less than 3.125mm.13rd layer need to deviate thickness 1.625mm, fold
The 3.25mm that adds thickness is greater than 3.125mm, this layer of curved surface directly cannot bias out.
Process is spread according to carbon fiber blade forming principle and layer, it is only necessary to which the curved surface for making a middle leaflet piece is cut away
It is had more after offset and carrys out sheet body, required sheet body can be obtained.13rd layer of layer of cloth cut-parts, detailed step are as follows:
Into CATIA shape-generative mode module, clicks " plane " order and make 10 planes, interplanar spacing on blade
For 90mm, " intersection " order is clicked, 10 planes is solved and carbon fiber blade entity 1 makes 10 intersection curves, see Fig. 4,
The normal direction of partial trace makes n straight line on each intersection curve, and there are two intersection points for every straight line and intersection curve, asks
The midpoint between two o'clock is solved, solves n midpoint altogether.Click n midpoint of " spline curve " chaining command, obtain one it is smooth
Curve, totally 10 curves.
" multi-section curve " order is clicked, 10 curves are successively selected, generates a smooth curved surface, this curved surface is for we
Required blade outer layer layer of cloth curved surface 3, the upper and lower surface of carbon fiber blade is extracted with " extraction " order respectively, and is inwardly biased
1.625mm, layer of cloth curved surface 4 after being deviated, carbon fiber blade upper and lower surfaces are spent small place intersection after rear, are seen
Fig. 3.Layer of cloth curved surface 4 after dividing the segmentation offset of curved surface 3 in the Divide command use is clicked, extra sheet body is removed, clicks " engagement " life
It enables and the upper and lower surface after offset segmentation is linked together.Click expansion order, the sheet body after selection engagement, required for obtaining
Cut-parts figure.
Claims (1)
1. a kind of method of carbon fiber structural layer of cloth cut-parts, which comprises the following steps:
1) n plane is uniformly chosen on carbon fiber blade (1) axis, n plane and carbon fiber blade (1) is made by software
Intersection curve, then by software solve intersection curve middle component curve；
2) the middle component curve of the n intersection curve done according to step 1, the middle component curve do peripheral curve top half
Normal direction straight line intersects two o'clock with peripheral curve, takes its midpoint and connects, and then generates and divide spoon of blade (2) equally；
3) blade outer layer layer of cloth curved surface (3) are extracted, inwardly biases ply gage, layer of cloth curved surface (4) after being deviated；The biasing
Ply gage is that carbon fiber blade (1) is made of n-layer layer of cloth, and ply gage is place n-th layer and first layer cloth interlamellar spacing；
4) with dividing equally spoon of blade (2) in step 2, layer of cloth curved surface (4) after segmentation offset removes extra curved surface, obtains institute
The curved surface needed, required curved surface are unfolded to obtain required cut-parts figure by CATIA software.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711359907.7A CN107962830B (en) | 2017-12-15 | 2017-12-15 | A kind of method of carbon fiber structural layer of cloth cut-parts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711359907.7A CN107962830B (en) | 2017-12-15 | 2017-12-15 | A kind of method of carbon fiber structural layer of cloth cut-parts |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107962830A CN107962830A (en) | 2018-04-27 |
| CN107962830B true CN107962830B (en) | 2019-08-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711359907.7A Active CN107962830B (en) | 2017-12-15 | 2017-12-15 | A kind of method of carbon fiber structural layer of cloth cut-parts |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101811580A (en) * | 2010-01-18 | 2010-08-25 | 中国航空工业集团公司北京航空制造工程研究所 | Baiting method of curve surface paving layer in composite material structure |
| CN102867082A (en) * | 2012-08-29 | 2013-01-09 | 西北工业大学 | Laying spreading method for composite material |
| CN104358708A (en) * | 2014-08-19 | 2015-02-18 | 航天材料及工艺研究所 | Carbon fiber composite foam core sandwich structure wind tunnel fan blade and molding method |
| CN106762820A (en) * | 2016-12-25 | 2017-05-31 | 宁波至高点工业设计有限公司 | A kind of method for designing of prismatic blade radial fan impeller |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016090405A1 (en) * | 2014-12-08 | 2016-06-16 | Peter John Murdoch | A method of forming a fibre metal composite component |
-
2017
- 2017-12-15 CN CN201711359907.7A patent/CN107962830B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101811580A (en) * | 2010-01-18 | 2010-08-25 | 中国航空工业集团公司北京航空制造工程研究所 | Baiting method of curve surface paving layer in composite material structure |
| CN102867082A (en) * | 2012-08-29 | 2013-01-09 | 西北工业大学 | Laying spreading method for composite material |
| CN104358708A (en) * | 2014-08-19 | 2015-02-18 | 航天材料及工艺研究所 | Carbon fiber composite foam core sandwich structure wind tunnel fan blade and molding method |
| CN106762820A (en) * | 2016-12-25 | 2017-05-31 | 宁波至高点工业设计有限公司 | A kind of method for designing of prismatic blade radial fan impeller |
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| Publication number | Publication date |
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| CN107962830A (en) | 2018-04-27 |
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