CN109676010A - A kind of processing method of carbon fibre composite plate connecting hole - Google Patents
A kind of processing method of carbon fibre composite plate connecting hole Download PDFInfo
- Publication number
- CN109676010A CN109676010A CN201811498560.9A CN201811498560A CN109676010A CN 109676010 A CN109676010 A CN 109676010A CN 201811498560 A CN201811498560 A CN 201811498560A CN 109676010 A CN109676010 A CN 109676010A
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- Prior art keywords
- connecting hole
- hole
- carbon fibre
- fibre composite
- composite plate
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Classifications
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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
- B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
- B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D28/00—Shaping by press-cutting; Perforating
- B21D28/24—Perforating, i.e. punching holes
- B21D28/26—Perforating, i.e. punching holes in sheets or flat parts
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- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Oral & Maxillofacial Surgery (AREA)
- Thermal Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Connection Of Plates (AREA)
- Insertion Pins And Rivets (AREA)
Abstract
The present invention relates to a kind of processing methods of carbon fibre composite plate connecting hole, method includes the following steps: 1) calculating the base diameter of connecting hole and the deflection in hole depth direction；2) connecting hole is processed according to the deflection of the base diameter of connecting hole and hole depth direction；3) in the hole week coating structure glue of connecting hole, and solidify at room temperature.Compared with prior art, the connecting hole that the present invention prepares bonding strength under the premise of meeting associated specifications greatly improves, the stress for reducing connecting hole hole week region is concentrated, reduce the risk of region carbon fibre composite rupture or layering failure, the time of hole week layering failure is postponed, to improve the carbon fibre composite components bonding strength in band connection hole, prolong the service life.
Description
Technical field
The invention belongs to carbon fibre composite components interconnection technique fields, are related to a kind of carbon fibre composite plate company
The processing method for connecing hole.
Background technique
Carbon fibre composite (abbreviation CFRP) has many advantages, such as that light weight, high intensity, collapse energy-absorption characteristic are good, in automobile
Field using more and more extensive, be that automobile realizes one of light-weighted common used material.In recent years, largely compound using carbon fiber
Material is as main more and more with the automobile of material.
Currently, the cost of carbon fibre composite is much higher than the metal materials such as steel plate, aluminium alloy and magnesium alloy, from mechanical property
From the point of view of energy, light weight effect and cost angle, carbon fibre composite and being used in mixed way for metal material will be Vehicle Materials
Main trend.Therefore, the interconnection technique of carbon fibre composite and other materials especially metal material is carbon fiber composite
Expect one of the key technology of development.There is hole connection type to have bonding strength high, weather-proof including riveting and bolting
Property, the advantages that heat-resisting quantity and durability are good, are the main connection types between carbon fibre composite components.There is hole connection side
Formula needs to process connecting hole on carbon fibre composite plate in advance, and existing carbon fibre composite plate method for drilling is main
There are punching and machine-building processing hole, and often only carry out grinding process after drilling, there is no other treatment measures.Due to making
The cutting of carbon fiber wire in carbon fibre composite plate is inevitably generated during hole, the fiber filament of hole week cutting is even
The military service for connecing hole can generate the failure such as local fracture, layering in the process, and hole week area more disconnected than base material is caused to connect in advance
Failure, to affect bonding strength and connection reliability.
The material of carbon fibre composite is not accounted for just because of existing carbon fibre composite plate method for drilling
Also without carrying out specially treated after drilling, thus the problem of connecting hole fails prior to base material often occurs for characteristic.Therefore,
According to the characteristics of carbon fibre composite and connection design requirement, the processing method of carbon fibre composite plate connecting hole is carried out
It improves, is one of current urgent problem to be solved.
Summary of the invention
It is an object of the present invention to overcome the above-mentioned drawbacks of the prior art and provide a kind of carbon fiber composites
The processing method of flitch connecting hole.
The purpose of the present invention can be achieved through the following technical solutions:
A kind of processing method of carbon fibre composite plate connecting hole, method includes the following steps:
1) base diameter of connecting hole and the deflection in hole depth direction are calculated；
2) connecting hole is processed according to the deflection of the base diameter of connecting hole and hole depth direction；
3) in the hole week coating structure glue of connecting hole, and solidify at room temperature.
Further, it in step 1), according to the mechanical connection design requirement of carbon fibre composite plate, is calculated using numerical value
Method predicts the bonding strength of carbon fibre composite plate, and calculates the deflection of connecting hole, obtains the base of connecting hole
This diameter and the deflection in hole depth direction.
The mechanical connection design requirement of carbon fibre composite plate mainly has:
1. the stress that should minimize carbon fibre composite plate is concentrated；2. end should be met away from/aperture > 2.5, width/hole
Diameter > 5, increase in the case where conditions permit as far as possible end away from back gauge；3. it is related with destruction is squeezed that connector should be made to generate as far as possible
Failure mode, rather than failure by shear or tensile failure；4. the laying direction of carbon fibre composite should as far as possible with connector direction
Unanimously；5. the plasticity of carbon fibre composite plate is poor, load reallocation ability is poor, and Multi-fasteners joint design should be as far as possible without using more
In the type of attachment of two rows of fasteners.
On carbon fibre composite plate the design of connecting hole need to meet destruction occur when plate prior to fastener destroy, i.e., by
Below 1., 2. formula it can be concluded that the base diameter D of connecting hole minimum License Value.
Had according to plate stretch failure condition:
Had according to sheet shearing failure condition:
1., 2. in formula, W is carbon fibre composite board width, and E is the end of carbon fibre composite plate away from t is carbon fiber
The thickness of composite panel, σT plateFor carbon fibre composite plate tensile strength, σS plateShearing resistance for carbon fibre composite plate is strong
Degree, σS nailFor fastener (bolt or rivet) shearing strength, 0.75D is fastener (bolt or rivet) outer diameter.
The deflection of connecting hole depth direction is determined by the base diameter of connecting hole, is selected according to the base diameter of connecting hole
The diameter of fastener (bolt or rivet) measures the variation of fastener (bolt or rivet) diameter after fastening, connection that you can get it
The deflection in hole depth direction.
Further, in step 1): the inner wall of the connecting hole is adapted with the lateral surface of fastener.
Further, the fastener is bolt or rivet.
Further, in step 2), connecting hole is processed by the way of punching, drilling, hole milling or bore hole.
Further, in step 3), the structure glue includes epoxy resin structure glue, polyurethanes structure glue or third
One of olefin(e) acid esters structure glue.Select the lesser structure glue of cubical contraction after solidifying.
Further, in step 3), shear strength >=carbon fibre composite plate after the structure adhesive curing is anti-
Tensile strength.
Connecting hole is the hole being provided on carbon fibre composite plate, and the hole be for rivet, be bolted or other
There is the connection hole of hole connection type.According to the base diameter of connecting hole and the deflection in hole depth direction, the company of can be designed
The shape and hole characteristic size in hole are connect, to use machining or material forming processing method on carbon fibre composite plate
Process connecting hole.
In the present invention, on the one hand passes through the shape of reasonable design connecting hole, increase connecting hole hole wall and fastener (riveting
Nail or bolt) contact area；On the other hand since structure glue has filled up the gap between connecting hole hole wall and fastener, in turn
Improve the cooperation precision between connecting hole and fastener.Hole circumferential stress concentration phenomenon is that carbon fibre composite plate mechanical connection is strong
The key constraints promoted are spent, connecting hole hole week on composite panel can all be alleviated by increasing contact area and improving cooperation precision
Stress concentration phenomenon, and then improve bonding strength.
Compared with prior art, the invention has the characteristics that:
1) present invention has fully considered the characteristic of carbon fibre composite plate, is connected by design carbon fibre composite plate
The shape and hole characteristic size in hole are connect, and applies one layer of structure glue after drilling and is strengthened, makes the connecting hole prepared full
Bonding strength greatly improves under the premise of sufficient associated specifications, and the stress for reducing connecting hole hole week region is concentrated, and reduces the area
The risk of the rupture of domain carbon fibre composite or layering failure has postponed the time of hole week layering failure, so that hole week region is not
It can first fail than other regions, to improve the carbon fibre composite components bonding strength in band connection hole, extend
Service life；
2) product development success rate is improved, shortens the development cycle, is conducive to carbon fibre composite part class product
Design and develop.
Detailed description of the invention
Fig. 1 is that CFRP and CFRP (Fig. 1 a), CFRP the and TRIP780 steel plate (Fig. 1 b) obtained using numerical computation method is adopted
With the deformation spirogram in the connecting hole week in the case of rivet interlacement；
Fig. 2 is the band connection hole CFRP plate after processing；
Fig. 3 is the band connection hole CFRP/ processed using traditional numeric-control method for milling (3a) and the method for the present invention (3b)
CFRP rivets picture of the sample after simple tension to deformation failure；
Fig. 4 is the band connection hole CFRP/ processed using traditional numeric-control method for milling (4a) and the method for the present invention (4b)
The maximum load figure that CFRP riveting sample can bear in simple tension.
Specific embodiment
The present invention is described in detail with specific embodiment below in conjunction with the accompanying drawings.The present embodiment is with technical solution of the present invention
Premised on implemented, the detailed implementation method and specific operation process are given, but protection scope of the present invention is not limited to
Following embodiments.
Embodiment 1:
A kind of processing method of carbon fibre composite plate connecting hole, comprising the following steps:
1) multiple to carbon fiber using numerical computation method according to the mechanical connection design requirement of carbon fibre composite plate
The bonding strength of condensation material plate is predicted, and calculates the deflection of connecting hole, obtains the base diameter and hole depth of connecting hole
The deflection for spending direction, is adapted the inner wall of connecting hole and the side of fastener (bolt)；
2) by the way of bore hole, connection is processed according to the deflection of the base diameter of connecting hole and hole depth direction
Hole；
3) in the hole week coating structure glue (epoxy resin structure glue) of connecting hole, and solidify at room temperature, structure glue is solid
Shear strength >=carbon fibre composite plate tensile strength after change.
Fig. 1 is that CFRP and CFRP (Fig. 1 a), CFRP the and TRIP780 steel plate (Fig. 1 b) obtained using numerical computation method is adopted
With the deformation spirogram in the connecting hole week in the case of rivet interlacement；Fig. 2 is the band connection hole CFRP plate after processing.
Fig. 3 is the band connection hole CFRP/ processed using traditional numeric-control method for milling (3a) and the present embodiment method (3b)
CFRP rivets picture of the sample after simple tension to deformation failure.As seen from Figure 3, using the processing of traditional numeric-control method for milling
The carbon fiber wire fracture and layering failure of highly significant has occurred CFRP plate rivet hole week；And use the examination of the method for the present invention processing
Sample is then that rivet is cut, and rivet hole week does not fail.This illustrates that the connecting hole of the method for the present invention processing has than riveting
Higher shear strength is followed closely, and the connecting hole of conventional method processing is lower than the shear strength of rivet, thus demonstrates present invention side
Method effectively improves the intensity in CFRP plate hole region.
Fig. 4 is the band connection hole CFRP/ processed using traditional numeric-control method for milling (4a) and the method for the present invention (4b)
The maximum load figure that CFRP riveting sample can bear in simple tension.From fig. 4, it can be seen that using the processing of numerical control milling method
The maximum tensile-sbear strength range of sample is in 2.72~3.62kN, average value 3.12kN；And use the band of the method for the present invention processing
The maximum tensile-sbear strength range of connecting hole CFRP plate sample is in 3.89~4.36kN, average value 4.20kN, it is seen that uses this hair
The bonding strength of the band connection hole CFRP plate of bright method processing is significantly improved.
Embodiment 2:
A kind of processing method of carbon fibre composite plate connecting hole, comprising the following steps:
1) multiple to carbon fiber using numerical computation method according to the mechanical connection design requirement of carbon fibre composite plate
The bonding strength of condensation material plate is predicted, and calculates the deflection of connecting hole, obtains the base diameter and hole depth of connecting hole
The deflection for spending direction, is adapted the inner wall of connecting hole and the side of fastener (rivet)；
2) by the way of hole milling, connection is processed according to the deflection of the base diameter of connecting hole and hole depth direction
Hole；
3) in the hole week coating structure glue (polyurethanes structure glue) of connecting hole, and solidify at room temperature, structure adhesive curing
Shear strength afterwards >=carbon fibre composite plate tensile strength.
Embodiment 3:
A kind of processing method of carbon fibre composite plate connecting hole, comprising the following steps:
1) multiple to carbon fiber using numerical computation method according to the mechanical connection design requirement of carbon fibre composite plate
The bonding strength of condensation material plate is predicted, and calculates the deflection of connecting hole, obtains the base diameter and hole depth of connecting hole
The deflection for spending direction, is adapted the inner wall of connecting hole and the side of fastener (bolt)；
2) by the way of drilling, connection is processed according to the deflection of the base diameter of connecting hole and hole depth direction
Hole；
3) in the hole week coating structure glue (esters of acrylic acid structure glue) of connecting hole, and solidify at room temperature, structure glue is solid
Shear strength >=carbon fibre composite plate tensile strength after change.
Embodiment 4:
A kind of processing method of carbon fibre composite plate connecting hole, comprising the following steps:
1) multiple to carbon fiber using numerical computation method according to the mechanical connection design requirement of carbon fibre composite plate
The bonding strength of condensation material plate is predicted, and calculates the deflection of connecting hole, obtains the base diameter and hole depth of connecting hole
The deflection for spending direction, is adapted the inner wall of connecting hole and the side of fastener (rivet)；
2) by the way of punching, connection is processed according to the deflection of the base diameter of connecting hole and hole depth direction
Hole；
3) in the hole week coating structure glue (epoxy resin structure glue) of connecting hole, and solidify at room temperature, structure glue is solid
Shear strength >=carbon fibre composite plate tensile strength after change.
The above description of the embodiments is intended to facilitate ordinary skill in the art to understand and use the invention.
Person skilled in the art obviously easily can make various modifications to these embodiments, and described herein general
Principle is applied in other embodiments without having to go through creative labor.Therefore, the present invention is not limited to the above embodiments, ability
Field technique personnel announcement according to the present invention, improvement and modification made without departing from the scope of the present invention all should be of the invention
Within protection scope.
Claims (7)
1. a kind of processing method of carbon fibre composite plate connecting hole, which is characterized in that method includes the following steps:
1) base diameter of connecting hole and the deflection in hole depth direction are calculated；
2) connecting hole is processed according to the deflection of the base diameter of connecting hole and hole depth direction；
3) in the hole week coating structure glue of connecting hole, and solidify at room temperature.
2. a kind of processing method of carbon fibre composite plate connecting hole according to claim 1, which is characterized in that step
1) in, according to the mechanical connection design requirement of carbon fibre composite plate, using numerical computation method, to carbon fibre composite
The bonding strength of plate is predicted, and calculates the deflection of connecting hole, obtains base diameter and the hole depth direction of connecting hole
Deflection.
3. a kind of processing method of carbon fibre composite plate connecting hole according to claim 1, which is characterized in that step
1) in: the inner wall of the connecting hole is adapted with the lateral surface of fastener.
4. a kind of processing method of carbon fibre composite plate connecting hole according to claim 3, which is characterized in that described
Fastener be bolt or rivet.
5. a kind of processing method of carbon fibre composite plate connecting hole according to claim 1, which is characterized in that step
2) in, connecting hole is processed by the way of punching, drilling, hole milling or bore hole.
6. a kind of processing method of carbon fibre composite plate connecting hole according to claim 1, which is characterized in that step
3) in, the structure glue includes one in epoxy resin structure glue, polyurethanes structure glue or esters of acrylic acid structure glue
Kind.
7. a kind of processing method of carbon fibre composite plate connecting hole according to claim 1, which is characterized in that step
3) shear strength >=carbon fibre composite plate tensile strength in, after the structure adhesive curing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811498560.9A CN109676010B (en) | 2018-12-08 | 2018-12-08 | Processing method of carbon fiber composite plate connecting hole |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811498560.9A CN109676010B (en) | 2018-12-08 | 2018-12-08 | Processing method of carbon fiber composite plate connecting hole |
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| CN109676010A true CN109676010A (en) | 2019-04-26 |
| CN109676010B CN109676010B (en) | 2019-12-27 |
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| CN201811498560.9A Active CN109676010B (en) | 2018-12-08 | 2018-12-08 | Processing method of carbon fiber composite plate connecting hole |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110435164A (en) * | 2019-07-19 | 2019-11-12 | 中国工程物理研究院化工材料研究所 | A method of it reducing fragile material open-celled structure stress and concentrates |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1986145A (en) * | 2006-12-22 | 2007-06-27 | 成都飞机工业（集团）有限责任公司 | Perforating process of composite carbon fiber material product |
| CN101670448A (en) * | 2009-09-16 | 2010-03-17 | 大连理工大学 | Method and device of disposing holes on carbon fiber composite material and meal material which are overlapped |
| JP2010179379A (en) * | 2009-02-03 | 2010-08-19 | Shigehiko Sakamoto | Drilling method |
| CN104999514A (en) * | 2014-04-21 | 2015-10-28 | 哈尔滨飞机工业集团有限责任公司 | Drilling method for structure assemblage of carbon fiber composite material |
| CN106650119A (en) * | 2016-12-27 | 2017-05-10 | 沈阳航空航天大学 | Prediction method of service life of drilling tool with CFRP(carbon fiber reinforced plastic) and titanium alloy laminated structure |
-
2018
- 2018-12-08 CN CN201811498560.9A patent/CN109676010B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1986145A (en) * | 2006-12-22 | 2007-06-27 | 成都飞机工业（集团）有限责任公司 | Perforating process of composite carbon fiber material product |
| JP2010179379A (en) * | 2009-02-03 | 2010-08-19 | Shigehiko Sakamoto | Drilling method |
| CN101670448A (en) * | 2009-09-16 | 2010-03-17 | 大连理工大学 | Method and device of disposing holes on carbon fiber composite material and meal material which are overlapped |
| CN104999514A (en) * | 2014-04-21 | 2015-10-28 | 哈尔滨飞机工业集团有限责任公司 | Drilling method for structure assemblage of carbon fiber composite material |
| CN106650119A (en) * | 2016-12-27 | 2017-05-10 | 沈阳航空航天大学 | Prediction method of service life of drilling tool with CFRP(carbon fiber reinforced plastic) and titanium alloy laminated structure |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110435164A (en) * | 2019-07-19 | 2019-11-12 | 中国工程物理研究院化工材料研究所 | A method of it reducing fragile material open-celled structure stress and concentrates |
| CN110435164B (en) * | 2019-07-19 | 2024-05-14 | 中国工程物理研究院化工材料研究所 | Method for reducing stress concentration of open pore structure of brittle material and structure thereof |
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| CN109676010B (en) | 2019-12-27 |
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