CN108995240A - A kind of forming method of composite material tubular component - Google Patents
A kind of forming method of composite material tubular component Download PDFInfo
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- CN108995240A CN108995240A CN201810634589.9A CN201810634589A CN108995240A CN 108995240 A CN108995240 A CN 108995240A CN 201810634589 A CN201810634589 A CN 201810634589A CN 108995240 A CN108995240 A CN 108995240A
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- 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
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
- B29C70/386—Automated tape laying [ATL]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Robotics (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The present invention relates to a kind of forming methods of composite material tubular component, belong to composite material preparation process technical field.Apply normal pressure during non-90 degree layer automatic placement of the invention, forms briquetting pressure.Laying briquetting pressure and winding tension are all scaled briquetting pressure, coordinated control is carried out by the briquetting pressure of offer, in conjunction with the requirement such as the width of practical prepreg tape, laying overall thickness, product diameter, winding tension and laying pressure are adjusted, achieve the purpose that briquetting pressure is almost the same, realizes the matching of laying winding process.
Description
Technical field
The present invention relates to a kind of forming methods of composite material tubular component, belong to composite material preparation process technology neck
Domain.
Background technique
There are mainly three types of moulding process for existing composite material tubular structure, and one kind is using prepreg craft laying molding work
Skill, one kind are System of Filament Winding Process.Another kind is laying moulding process.Prepreg craft laying moulding process laying angle
Precision is low, laying unstable quality, shaping efficiency are lower；Winding range is limited when System of Filament Winding Process forms tubular construction
System, not can be carried out local winding；System of Filament Winding Process profile angle is restricted, and not can be carried out low-angle winding；Fiber twines
Around molding process requirement band Dome winding, there are fiber wastes；Laying moulding process forms pre- when wide-angle (60 ° or more) laying
The leaching material proportion of goods damageds are high, and low efficiency when 90 ° of hoop layers of molding.
Summary of the invention
Technology of the invention solves the problems, such as: overcome the deficiencies in the prior art, proposes a kind of composite material tubular component
Forming method, this method profile angle precision is high, and Forming Quality is stablized, and the raw material proportion of goods damageds are low, and shaping efficiency is high, and can be in cylinder
Shape structure any position carries out local reinforcement.
The technical solution of the invention is as follows:
A kind of the step of forming method of composite material tubular component, this method includes:
(1) the molding formpiston of composite material tubular component is made；
(2) cut as width by prepreg is d1Winding band and width be d2Laying；
Wherein, d1=2 π rcot α, r are molding formpiston outer diameter, and α is winding angle, preferably 89.0 °~89.7 ° of α；
d2The central angle of=2 π r β/360, β layings, preferred 10-15 ° of β；
(3) width for using step (2) to obtain is d2The molding male mold surfaces that make in step (1) of laying carry out laying
(laying angle is preferably 0-60 °) defines the process to complete a non-90 degree formable layer (laying forming), completes p non-90 degree
The width for using step (2) to obtain on laying surface after formable layer is d1Winding band be wound, define the process for complete
One 90 ° of formable layer (Wrapping formed) completes q 90 ° of formable layers；P is 1,2 or 3, q 1,2 or 3；P non-90 degree formable layer
Overall thickness is not more than 0.6mm, and the overall thickness of q 90 ° of formable layers is not more than 0.6mm；
The step can be with are as follows:
The width for using step (2) to obtain is d1Laying be wound in the molding male mold surfaces that step (1) makes, it is fixed
The adopted process is to complete 90 ° of formable layers (Wrapping formed), uses step in winding layer surface after q 90 ° of formable layers of completion
(2) width obtained is d2Laying carry out laying (laying angle is preferably 0-60 °), define the process for complete one it is non-
90 ° of formable layers (laying forming) complete p 90 ° of formable layers；P is 1,2 or 3, q 1,2 or 3；The total thickness of p non-90 degree formable layer
Degree is not more than 0.6mm, and the overall thickness of q 90 ° of formable layers is not more than 0.6mm；
(4) step (3) are repeated, i.e., non-90 degree formable layer and 90 ° of formable layers are setting value up to forming the number of plies alternately
N, fiber overall thickness are setting value tf；
(5) product for obtaining step (4) carries out curing molding, and demoulding obtains composite material tubular component.
Carry out 90 ° of formable layers it is i.e. Wrapping formed when winding tension determination method are as follows:
Wherein, T (tγ): winding is with a thickness of tγWhen winding tension；
I=1,2,3..., n, tiFor i-th layer of fiber thickness；
tγ: theγFiber overall thickness after the completion of layer winding；
K=σ0(tf+tMf), tfFor fiber overall thickness；σ0For fiber initial tension value；
tMfFiber equivalent thickness is converted to for molding formpiston thickness；EMFor form formpiston elasticity modulus,
EfFor the elasticity modulus of fiber, tMFor the thickness (wall thickness) for forming formpiston；
The determination method of laying pressure when progress non-90 degree formable layer, that is, laying forming are as follows:
In formula: F is positive pressure；K is technological coefficient, it is proposed that being worth is 0.5~3；d2For the width of laying, i.e. non-90 degree layer
Prepreg width；H is pressure roller contact width；T(tγ) it is winding tension, RγIt isγLayer laying when have become fiber type overall thickness with
Form the sum of the outer diameter of formpiston.
Method of the invention make first molding formpiston, then prepreg is cut, when being cut according to institute at
Prepreg is cut into width required for broadband winding and automatic placement by the outer diameter of type Cylinder shape constructional element.When cutting prepreg, build
The prepreg width of view broadband winding makes 89.0 °~89.7 ° of winding angle, and the prepreg width of automated tape-laying is in laying pair
The central angle answered is less than 15 °.Finally carry out Cylinder shape constructional element molding.Cylinder shape constructional element molding include 90 ° of formable layers and non-90 degree layer at
Type, 90 ° of layers and non-90 degree layer alternately form.90 ° of layers of Cylinder shape constructional element are formed using broadband winding technology.It is needed during 90 ° of formable layers
Apply winding tension；Non-90 degree layer is formed using automated tape-laying technology, needs to apply positive compression during non-90 degree formable layer；
90 ° of layer winding tensions and non-90 degree layer forward direction compression need to be mutually matched.Cylinder shape constructional element solidification is carried out again.According to the tree of prepreg
Resin system is formulated curing cycle and is solidified to Cylinder shape constructional element.
The Cylinder shape constructional element diameter is greater than 800mm, and length is greater than 0.5m, to guarantee shaping efficiency, it is proposed that Cylinder shape constructional element is long
Degree is greater than 6m.
The non-90 degree layer includes 0 ° to the 89 ° angled layer of institute, all non-90 degree layers can high-precision laying, to guarantee molding
Efficiency and prepreg utilization rate, non-90 degree optimized scope are 0 °~60 °.
The Cylinder shape constructional element can carry out reinforcement in any position of component.
Alternately, the same continuous laying of angle layer is no more than 3 layers, and thickness is no more than for the width winding and auto-spreading
0.6mm。
Beneficial effect
(1) present invention can be designed so that each layer fiber of composite material from inside to outside is in certain by gradient tension
Change of gradient, final purpose is that each layer fiber is made to have identical prestressing force, so that the entirety for playing composite material at work is held
Loading capability.
(2) apply normal pressure during non-90 degree layer automatic placement of the invention, form briquetting pressure.Laying is formed and is pressed
Power and winding tension are all scaled briquetting pressure, coordinated control are carried out by the briquetting pressure of offer, in conjunction with the width of practical prepreg tape
The requirement such as degree, laying overall thickness, product diameter, is adjusted winding tension and laying pressure, reaches briquetting pressure basic one
The purpose of cause realizes the matching of laying winding process.
(3) the molding Cylinder shape constructional element molded test verifying of method of the invention, such briquetting pressure matching way rationally may be used
Row, and ensure that the laying density of the big thickness sidewall of composite tube, improve Forming Quality.Therefore the process at
The big thickness large-sized composite material Cylinder shape constructional element of type has great advantage on molding rate and Forming Quality.
(4) laying efficiency of the invention has reached 27kg/h, and broadband winding efficiency has reached 45kg/h, laying laying angle
Precision has been increased to ± 0.2 ° by ± 2 ° of manual laying.
(5) method of the invention first prepares prepreg, prepares molding formpiston.Composite material tubular molding component includes 90 °
Formable layer and non-90 degree formable layer, the width that prepreg is cut into needs is spare, and prepreg cuts width according to Cylinder shape constructional element half
Diameter determines, it is proposed that 90 ° of layer prepreg width make 89.0 °~89.7 ° of winding angle, and when non-90 degree layer prepreg laying is corresponding
Central angle is less than 15 °.Non-90 degree layer is formed using automated tape-laying in Cylinder shape constructional element forming process, and 90 ° of layers are using circumferential broadband winding
Molding, automated tape-laying and broadband winding are alternately.Cylinder shape constructional element is solidified after the completion of all formable layers.
(6) present invention describes a kind of suitable for composite material tubular component automatic molding process method, belongs to composite wood
Expect fabricating technology field.The process is by automated tape-laying technology and broadband winding technology in composite material tubular component
Matching optimization is carried out in forming process, and is applied to the development and production of Cylinder shape constructional element, improves the paving of composite material tubular component
Layer angle precision, compactness and shaping efficiency, the nearly half of molding component cycle time.
Detailed description of the invention
Fig. 1 is method flow schematic diagram of the invention.
Specific embodiment
Composite material tubular molding component process flow is as shown in Figure 1.Prepreg is first prepared, molding formpiston is prepared.It is compound
The molding of material Cylinder shape constructional element includes 90 ° of formable layers and non-90 degree formable layer, and the width that prepreg is cut into needs is spare, preimpregnation
Material cutting width is determined according to Cylinder shape constructional element radius, it is proposed that 90 ° of layer prepreg width make 89.0 °~89.7 ° of winding angle, non-
Corresponding central angle is less than 15 ° when 90 ° of layer prepreg layings.In Cylinder shape constructional element forming process non-90 degree layer using automated tape-laying at
Type, 90 ° of layers are Wrapping formed using circumferential broadband, and automated tape-laying and broadband winding are alternately.To cylinder after the completion of all formable layers
Shape component is solidified, and specific implementation step is as follows:
(1) production molding formpiston.
(2) prepreg is cut.Prepreg is cut into broadband winding and automatic paving according to the radius of formed Cylinder shape constructional element
Required width is put, when cutting prepreg, it is proposed that the prepreg width of broadband winding makes 89.0 °~89.7 ° of winding angle,
The prepreg width of automated tape-laying in laying corresponding central angle less than 15 °.
(3) Cylinder shape constructional element forms.Cylinder shape constructional element non-90 degree layer is formed using automated tape-laying, and 90 ° of layers are using circumferential broadband winding
Molding, automated tape-laying and broadband winding are alternately.
The Composite molding for realizing laying and winding, need to solve the problems, such as the process matching of two kinds of process combinings, this
With including match materials and processing parameter matching.To avoid matching problem caused by material, the molding Cylinder shape constructional element of Composite is adopted
It is with same material, i.e., Wrapping formed identical with the prepreg system of laying molding use.Processing parameter matching mainly includes into
Type temperature and briquetting pressure.Forming temperature is matched because material system is identical, therefore essentially identical to two kinds of systems, as long as control room temperature
?.Briquetting pressure fits through the circumferential winding tension of application and laying normal pressure is realized.
Apply winding tension, the tension force system that winding tension uses gradient to successively decrease in 90 ° of layer circumferential direction width winding processes
Degree, design principle are as follows:
Composite layer is divided into n-layer, first layer to each winding tension of outermost layer is followed successively by T1, T2 ... ... Tn.Each layer
The actual stress of fiber is the pressure that each layer winding tension generates the tensile stress itself generated and whole outer layer winding tensions to it
The sum of stress can be obtained by the derivation of equation, make fiber winding forming backward pull state uniform, the application formula of every layer of tension
Are as follows:
In formula: K=σ0(tf+tMf)；
tiFor i-th layer of fiber thickness
In formula: T (tγ): winding is with a thickness of tγWhen winding tension；
tγ: theγFiber overall thickness after the completion of layer winding；
tf: fiber overall thickness (including non-90 degree layer)；
σ0: fiber initial tension value
tMf: fiber equivalent thickness is converted to for metal die thickness.
It can be designed so that each layer fiber of composite material from inside to outside is in certain change of gradient by gradient tension,
Final purpose is that each layer fiber is made to have identical prestressing force, to play the integrated carrying ability of composite material at work.
Apply normal pressure during non-90 degree layer automatic placement, forms briquetting pressure.By laying briquetting pressure and winding tension
It is all scaled briquetting pressure, carries out coordinated control, width, laying total thickness in conjunction with practical prepreg tape by the briquetting pressure of offer
The requirement such as degree, product diameter, is adjusted winding tension and laying pressure, achievees the purpose that briquetting pressure is almost the same, real
The matching of laying winding process is showed.Non-90 degree calculation of pressure method are as follows:
Non-90 degree layer positive pressureIn formula: F is positive pressure；K is technological coefficient, it is proposed that being worth is 0.5
~3；d2For non-90 degree layer prepreg laying width；H is pressure roller contact width；T(tr) it is 90 ° of layer tension, RλTo be spread for γ layers
Fiber type overall thickness is had become when putting and forms the sum of the outer diameter of formpiston.
It is verified through Cylinder shape constructional element molded test, such briquetting pressure matching way reasonable, and ensure that composite tube is big
The laying density of thickness sidewall, improves Forming Quality.Therefore the process is compound for forming big thickness large scale
Material Cylinder shape constructional element has great advantage on molding rate and Forming Quality.
For the automatic forming technology that project is related to, circumferential broadband winding technology is broken through respectively, tubular construction is spread automatically
The band technologies such as technique, are then directed to tubular construction class product, complete the integrated of broadband winding and automated tape-laying technology, solve
The automatic forming technology of composite material tubular structure, automated tape-laying efficiency have reached 27kg/h, and broadband winding efficiency reaches
45kg/h, automated tape-laying laying angle precision have been increased to ± 0.2 ° by ± 2 ° of manual laying.
(4) Cylinder shape constructional element solidifies.According to the resin system of prepreg, formulates curing cycle and Cylinder shape constructional element is solidified.
Embodiment
A long 7m, radius 2m, the Cylinder shape constructional element of thickness 18mm, the tubular construction have been formed using this moulding technique
Preceding 5 layers of ply stacking-sequence is [90/0/90/0/90].90 ° of layers use Wrapping formed mode, wind the width d of band1=50mm, it is real
Border winding angle is 89.5 °, and 0 ° uses laying molding mode, the width d of laying2=150mm, 90 ° of winding tensions are 9.2N/
The pressure of mm, 9N/mm, 8.8N/mm, 0 ° of layings is 19.8N and 19.4N.The Cylinder shape constructional element molding cycle is 12 days, more manual than former
Shorten nearly half within molding cycle 23 days.
The whole cylinder of Cylinder shape constructional element after molding is detected using supersonic damage-free detection method, testing result shows that component is whole
Body without layering, loose, stomata the defects of, spot sampling is carried out to component, metallographic test is made, metallographic observation shows structure
The porosity of part is lower than 0.3%.
Claims (10)
1. a kind of forming method of composite material tubular component, it is characterised in that the step of this method includes:
(1) the molding formpiston of composite material tubular component is made；
It (2) is winding band and laying by prepreg cutting；
(3) laying obtained using step (2) carries out laying forming, laying forming in the molding male mold surfaces that step (1) makes
The winding band progress obtained after the completion on laying surface using step (2) is Wrapping formed, is winding band table after the completion of Wrapping formed
Face carries out laying forming again, is wound molding again later；
(4) laying forming in step (3) and it is Wrapping formed alternately, until molding the number of plies and fiber overall thickness meet design
It is required that；
(5) product that step (4) obtains is solidified, demoulds, obtains composite material tubular component.
2. a kind of forming method of composite material tubular component according to claim 1, it is characterised in that: the step
(3) in, molding is wound in the molding male mold surfaces that step (1) makes using the winding band that step (2) obtain first, is wound
Laying forming is carried out using the laying that step (2) obtain in winding belt surface after the completion of molding, laying forming is after the completion in laying
Surface is wound molding, carries out laying forming again later.
3. a kind of forming method of composite material tubular component according to claim 1 or 2, it is characterised in that: described
In step (2), the width for winding band is d1, d1=2 π r cot α, r are molding formpiston outer diameter, and α is winding angle.
4. a kind of forming method of composite material tubular component according to claim 3, it is characterised in that: α be 89.0 °~
89.7°。
5. a kind of forming method of composite material tubular component according to claim 1 or 2, it is characterised in that: described
In step (2), the width of laying is d2, d2=2 π r β/360, β are the central angle of laying, and r is molding formpiston outer diameter.
6. a kind of forming method of composite material tubular component according to claim 5, it is characterised in that: β 10-15.
7. a kind of forming method of composite material tubular component according to claim 1 or 2, it is characterised in that: described
In step (3), when laying forming, laying angle is 0-60 °, and laying number of plies when each laying forming is 1,2 or 3, is spread every time
Lay down fibre overall thickness when molding is put no more than 0.6mm.
8. a kind of forming method of composite material tubular component according to claim 1 or 2, it is characterised in that: described
In step (3), the determination method of laying pressure when laying forming are as follows:
In formula: F is laying pressure；K is technological coefficient, it is proposed that being worth is 0.5~3；d2For the width of laying, i.e. non-90 degree layer prepreg
Width；H is pressure roller contact width；T(tγ) it is winding tension, RγIt isγFiber type overall thickness and molding sun are had become when layer laying
The sum of outer diameter of mould.
9. a kind of forming method of composite material tubular component according to claim 1 or 2, it is characterised in that: described
In step (3), winding layer number when Wrapping formed every time is 1,2 or 3, and winding fiber overall thickness when Wrapping formed every time is little
In 0.6mm.
10. a kind of forming method of composite material tubular component according to claim 1 or 2, it is characterised in that: described
In step (3), it is wound the determination method of winding tension when molding are as follows:
Wherein, T (tγ): winding is with a thickness of tγWhen winding tension；
I=1,2,3..., n, tiFor i-th layer of fiber thickness；
tγ: theγFiber overall thickness after the completion of layer winding；
K=σ0(tf+tMf), tfFor fiber overall thickness；σ0For fiber initial tension value；
tMfFiber equivalent thickness is converted to for molding formpiston thickness；EMFor the elasticity modulus for forming formpiston, EfFor
The elasticity modulus of fiber, tMFor the wall thickness for forming formpiston.
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|---|---|---|---|
| CN201810634589.9A CN108995240B (en) | 2018-06-20 | 2018-06-20 | Forming method of composite material cylindrical component |
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| CN201810634589.9A CN108995240B (en) | 2018-06-20 | 2018-06-20 | Forming method of composite material cylindrical component |
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Cited By (2)
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| CN111331877A (en) * | 2020-02-17 | 2020-06-26 | 浙江理工大学 | Preparation method of variable-stiffness composite material spiral spring |
| CN115557743A (en) * | 2022-11-04 | 2023-01-03 | 江苏宇航板业有限公司 | Production method of single-blank calcium silicate cement board |
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| CN115557743A (en) * | 2022-11-04 | 2023-01-03 | 江苏宇航板业有限公司 | Production method of single-blank calcium silicate cement board |
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| CN108995240B (en) | 2021-02-09 |
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