CN106003876A - Composite avoiding tearing during riveting and laying method - Google Patents
Composite avoiding tearing during riveting and laying method Download PDFInfo
- Publication number
- CN106003876A CN106003876A CN201610329777.1A CN201610329777A CN106003876A CN 106003876 A CN106003876 A CN 106003876A CN 201610329777 A CN201610329777 A CN 201610329777A CN 106003876 A CN106003876 A CN 106003876A
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- CN
- China
- Prior art keywords
- prepreg
- fabric
- unidirectional
- composite
- layers
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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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
- B32B5/12—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 characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
-
- 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
- B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
-
- 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
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/02—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by a sequence of laminating steps, e.g. by adding new layers at consecutive laminating stations
-
- 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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/50—Properties of the layers or laminate having particular mechanical properties
- B32B2307/582—Tearability
- B32B2307/5825—Tear resistant
Landscapes
- Laminated Bodies (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention relates to the field of materials, in particular to a composite avoiding tearing during riveting and a laying method. The composite avoiding tearing during riveting comprises one or more layers of fiber fabric and multiple layers of unidirectional fiber prepreg from bottom to top sequentially, wherein the warp direction of each layer of fiber fabric and the fiber direction of the unidirectional fiber prepreg are arranged at different angles with a preset horizontal plane during laying. By means of the technical scheme, the problems that the production schedule and the quality are seriously affected due to blind inserting and mounting of a metal gasket in the prior art are solved, a metal piece is needless to be assembled, two layers or more layers of plates can be directly connected through a blind rivet, and the conditions that the connecting strength is reduced and even the connection fails due to the fact that an orifice of the composite is torn because of expansion of the blind rivet cannot be caused.
Description
Technical field
The present invention relates to Material Field, particularly to composite and the laying method of a kind of anti-staking tear.
Background technology
Composite board member uses self-plugging rivet to typically require the expansion at self-plugging rivet when connecting two-layer or multi-layer sheet
End installs metallic gasket additional, to protect the composite panel aperture of self-plugging rivet expanding end not to be torn.
One assembly is made up of big L/D ratio carbon fiber square tube and metal U-shaped part, and two components need to use the mode of riveting
Link together, owing to carbon fiber square tube is the closure member of big L/D ratio, it is impossible to use pressure-riveting process to connect molding, can only adopt
Using staking technique, the i.e. molding of self-plugging rivet riveting, carrying out this assembly technology in open space is more ripe skill
Art, however narrow and small or close space, due to cannot or inconvenience install metallic gasket, this assembly technology just can not use or
Efficiency is the lowest.
According to the riveting requirement of traditional carbon fiber board, need to install additional metallic gasket at carbon fiber back, but due to behaviour
Make narrow space, use special fixture to stick with glue in advance in rivet hole position and connect the method for metallic gasket and install additional, due to bonding gold
The quantity belonging to pad is a lot, and workload is very big, and production efficiency is low, and owing to blindmate is installed, after curing of the glue, the most easily goes out
Drop phenomenon, manufacturing schedule and quality of existing metallic gasket is severely impacted.
Summary of the invention
In order to when solving blindmate installation in prior art, metallic gasket drops phenomenon, manufacturing schedule and quality by serious shadow
The problem rung, the invention provides composite and the laying method of a kind of anti-staking tear.
The present invention provides the composite that a kind of anti-staking tears, be followed successively by from down to up one or more layers fabric with
And multilamellar unidirectional fiber prepregs, the longitudinal of described every layer of fabric and the machine direction of unidirectional fiber prepregs are with pre-
If horizontal plane becomes different angles to lay.
Present invention also offers the laying method of the composite of a kind of anti-staking tear, comprise the following steps:
Determine one or more layers fabric prepreg and multilamellar unidirectional fiber prepregs respectively lays the number of plies and side
To, wherein, the longitudinal of described every layer of fabric becomes not with preset level face with the machine direction of unidirectional fiber prepregs
Same angle；
According to the described number of plies and direction, one or more layers fabric prepreg and multilamellar unidirectional fiber prepregs are existed
Lay on mould, and be compacted.
The present invention has the beneficial effect that:
In the composite that the present invention provides, every layer of fabric and unidirectional fiber prepregs fabric are respectively provided with respective side
To, solve in prior art owing to when blindmate is installed, metallic gasket drops the manufacturing schedule caused and quality is severely impacted
Problem, it is possible to need not install sheet metal additional, directly use self-plugging rivet to connect two-layer or multi-layer sheet (composite panel/composite wood
Flitch, or composite panel/metallic plate), will not produce simultaneously tear due to the expansion of self-plugging rivet composite aperture, from
And cause bonding strength reduction, even Joint failure.
Accompanying drawing explanation
Fig. 1 is the structural representation of the composite of the anti-staking tear of product embodiments of the present invention；
Fig. 2 is composite and the attachment structure signal of metal U-shaped part of the anti-staking tear of the inventive method embodiment
Figure；
Fig. 3 is the laying method flow chart of the composite of the anti-staking tear of the inventive method embodiment；
Fig. 4 is the structural representation of pull-off test carbon fiber board in test example of the present invention；
Fig. 5 is the structural representation of tensile shear testing carbon fiber board in test example of the present invention；
Fig. 6 is the top view pulling sample in test example of the present invention；
Fig. 7 is the sectional view drawing in test example of the present invention and cutting sample.
Detailed description of the invention
In order to when solving blindmate installation in prior art, metallic gasket drops phenomenon, manufacturing schedule and quality by serious shadow
The problem rung, the invention provides composite and the laying method of a kind of anti-staking tear, below in conjunction with accompanying drawing and enforcement
Example, is further elaborated to the present invention.Should be appreciated that specific embodiment described herein is only in order to explain this
Bright, do not limit the present invention.
Product embodiments
According to embodiments of the invention, it is provided that the composite of a kind of anti-staking tear, Fig. 2 is that product of the present invention is implemented
The structural representation of the composite of the anti-staking tear of example, as in figure 2 it is shown, tear according to the anti-staking of product embodiments of the present invention
The composite split, including being followed successively by one or more layers fabric and multilamellar unidirectional fiber prepregs from down to up, described
The longitudinal of every layer of fabric becomes different angles to lay with the machine direction of unidirectional fiber prepregs with preset level face, with
Under the modules of the embodiment of the present invention is described in detail.
Specifically, the composite of the anti-staking tear of product embodiments of the present invention includes 1 layer of fibre from down to up
Dimensional fabric and 16 layers of unidirectional fiber prepregs, wall thickness is 2.75mm (2.45mm～2.75mm), in Fig. 2 i-th layer expression the
Any one layer between one layer and n-th layer, n=17.Ply stacking-sequence be [0 ° /+45 °/-45 °/0 °/0 °/90 °/0 °/-45 °/0 °/
+ 45 °/0 °/0 °/90 °/0 °/0 °/-45 ° /+45 °], 0 ° of direction is tubular length direction.
Described fabric includes carbon fibre fabric, glass fiber cloth, aramid fabric；Described unidirectional fibre presoaks
Material includes unidirectional carbon prepreg, one-way glass fiber prepreg material, unidirectional aramid fiber prepreg etc..
Preferably, described unidirectional carbon is carbon fiber T700, and table 1 is the key property of carbon fiber T700.
Table 1
The composite (alternatively referred to as carbon fiber square tube) of the anti-staking tear of product embodiments of the present invention can be with metal U
Shape part is assembled, uses self-plugging rivet riveting molding, and without installing metallic gasket additional, will not produce due to self-plugging rivet is swollen simultaneously
Swollen and tear composite aperture thus cause bonding strength to reduce, even Joint failure, Fig. 2 is the inventive method embodiment
Anti-staking tear composite and the attachment structure schematic diagram of metal U-shaped part.
Embodiment of the method
According to embodiments of the invention, it is provided that the laying method of the composite of a kind of anti-staking tear, Fig. 3 is this
The laying method flow chart of the composite of the anti-staking tear of bright embodiment of the method, as it is shown on figure 3, real according to the inventive method
The laying method of the composite executing the anti-staking tear of example includes processing as follows:
Step 302, determines laying of one or more layers fabric prepreg and multilamellar unidirectional fiber prepregs respectively
The number of plies and direction, wherein, the longitudinal of described every layer of fabric becomes with preset level face with the machine direction of unidirectional fibre
Different angles.
Specifically, one or more layers fabric prepreg and the laying layer of multilamellar unidirectional fiber prepregs are determined respectively
Number and direction comprise the following steps: the strength and stiffness of the composite torn according to anti-staking require to determine one layer or many respectively
Layer fabric prepreg and multilamellar unidirectional fiber prepregs lay the number of plies and direction.
Preferably, determine that the number of plies of laying of fabric prepreg and multilamellar unidirectional fiber prepregs includes following step
Rapid: described composite includes 1 layer of fabric prepreg from down to up and 16 layers of unidirectional fiber prepregs.
It is further preferred that determine the ply stacking-sequence of fabric prepreg and multilamellar unidirectional fiber prepregs for [0 ° /+
45°/-45°/0°/0°/90°/0°/-45°/0°/+45°/0°/0°/90°/0°/0°/-45°/+45°]。
Described fabric prepreg includes that carbon fibre fabric prepreg, glass fiber cloth prepreg, aramid fiber are knitted
Thing prepreg, preferably thickness are the carbon fibre fabric prepreg (thickness after molding) of 0.3mm；Described unidirectional fiber prepregs bag
Include unidirectional carbon prepreg, one-way glass fiber prepreg material, the Unidirectional of unidirectional aramid fiber prepreg, preferably 0.15mm
Fiber prepreg material (thickness after molding).
Knit for the fiber in product embodiments after the cured molding of fabric prepreg in the inventive method embodiment
Thing, is the unidirectional fibre in product embodiments after the cured molding of unidirectional fiber prepregs in embodiment of the method.
Step 304, according to the described number of plies and direction by one or more layers fabric prepreg and multilamellar unidirectional fibre
Prepreg prepreg lays on mould, and is compacted.
In order to better illustrate embodiment of the method, provide example 1.
The preparation method of the composite that example 1 tears for anti-staking shown in Fig. 2, possesses and comprises the following steps:
The carbon fibre fabric prepreg cut and unidirectional carbon prepreg are laid on core, was laying
Journey needs be compacted at any time, and lays in the following order:
[0°/+45°/-45°/0°/0°/90°/0°/-45°/0°/+45°/0°/0°/90°/0°/0°/-45°/+45°]。
Test example
Preparing two kinds of carbon fibre composite plates according to the method for the inventive method embodiment, Fig. 4 is test example of the present invention
The structural representation of middle pull-off test carbon fiber board, a size of 20 × 30mm, thickness is 2.75mm；Fig. 5 is that the present invention tests
The structural representation of tensile shear testing carbon fiber board, a size of 36mm × 135mm in example, thickness is 2.75mm.
Fig. 6 test example of the present invention pulls the structural representation of sample, Fig. 7 test example of the present invention draws the structure cutting sample
Schematic diagram, is assembled into by Fig. 6 and Fig. 7 with φ 4 stainless steel self-plugging rivet and pulls sample and draw and cut sample.Pull sample and do 10 altogether
Part, wherein 5 expanding ends at self-plugging rivet install the riveting of φ 4 metallic gasket, do not install metallic gasket and directly rivet for another 5；
Drawing and cut sample and do 10 altogether, wherein 5 expanding ends at self-plugging rivet install the riveting of φ 4 metallic gasket, do not install metal for another 5
Pad directly rivets；
20 groups of samples carry out pull-off test and tensile shear testing respectively, and the pulling-out force needed for test rivet destroys is cut with drawing
Power, table 2 is the original experiment data of pull-off test and tensile shear testing.
Table 2
Seen by table 2 data: carbon fibre composite backboard portion has, without the equal value difference of shearing that draws of metallic gasket be
0.016KN；Back has, be 0.018KN without the equal value difference of pulling-out force of metallic gasket；Their difference is the least, under normal conditions,
The two version can be exchanged, its pulling-out force and draw shearing to be satisfied by serviceability requirement.
Obviously, those skilled in the art can carry out various change and the modification essence without deviating from the present invention to the present invention
God and scope.So, if these amendments of the present invention and modification belong to the scope of the claims in the present invention and equivalent technologies thereof
Within, then the present invention is also intended to comprise these change and modification.
Claims (10)
1. the composite of anti-staking tear, it is characterised in that be followed successively by from down to up one or more layers fabric with
And multilamellar unidirectional fiber prepregs, the longitudinal of described every layer of fabric and the machine direction of unidirectional fiber prepregs are with pre-
If horizontal plane becomes different angles to lay.
The composite of anti-staking the most according to claim 1 tear, it is characterised in that include 1 layer of fibre from down to up
Dimensional fabric and 16 layers of unidirectional fiber prepregs.
Anti-staking the most according to claim 2 tear composite, ply stacking-sequence be [0 ° /+45 °/-45 °/0 °/0 °/
90°/0°/-45°/0°/+45°/0°/0°/90°/0°/0°/-45°/+45°]。
The composite of anti-staking the most according to claim 1 tear, it is characterised in that described fabric includes that carbon is fine
Dimensional fabric, glass fiber cloth, aramid fabric.
The composite of anti-staking the most according to claim 1 tear, it is characterised in that described unidirectional fiber prepregs bag
Include unidirectional carbon prepreg, one-way glass fiber prepreg material, unidirectional aramid fiber prepreg.
6. the laying method of the composite of an anti-staking tear, it is characterised in that
Determine one or more layers fabric prepreg and multilamellar unidirectional fiber prepregs respectively lays the number of plies and direction, its
In, the longitudinal of described every layer of fabric becomes different angle with the machine direction of unidirectional fiber prepregs from preset level face
Degree；
According to the described number of plies and direction by one or more layers fabric prepreg and multilamellar unidirectional fiber prepregs at mould
On lay, and be compacted.
7. laying method as claimed in claim 6, it is characterised in that determine respectively one or more layers fabric prepreg with
And the laying number of plies of multilamellar unidirectional fiber prepregs and direction specifically include following steps:
The strength and stiffness of the composite torn according to anti-staking require to determine one or more layers fabric prepreg respectively
And multilamellar unidirectional fiber prepregs lay the number of plies and direction.
8. laying method as claimed in claim 7, it is characterised in that determine fabric prepreg and multilamellar unidirectional fibre
The number of plies of laying of prepreg comprises the following steps:
Described composite includes 1 layer of fabric prepreg from down to up and 16 layers of unidirectional fiber prepregs.
9. laying method as claimed in claim 7 or 8, it is characterised in that determine that fabric prepreg and multilamellar are unidirectional
The ply stacking-sequence of fiber prepreg material be [0 ° /+45 °/-45 °/0 °/0 °/90 °/0 °/-45 °/0 ° /+45 °/0 °/0 °/90 °/0 °/
0°/-45°/+45°]。
10. laying method as claimed in claim 6, it is characterised in that described fabric prepreg includes carbon fibre fabric
Prepreg, glass fiber cloth prepreg, aramid fabric prepreg；Described unidirectional fiber prepregs includes unidirectional carbon
Prepreg, one-way glass fiber prepreg material, unidirectional aramid fiber prepreg.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610329777.1A CN106003876A (en) | 2016-05-18 | 2016-05-18 | Composite avoiding tearing during riveting and laying method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610329777.1A CN106003876A (en) | 2016-05-18 | 2016-05-18 | Composite avoiding tearing during riveting and laying method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106003876A true CN106003876A (en) | 2016-10-12 |
Family
ID=57097872
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610329777.1A Pending CN106003876A (en) | 2016-05-18 | 2016-05-18 | Composite avoiding tearing during riveting and laying method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108297458A (en) * | 2018-04-04 | 2018-07-20 | 吉林大学 | Carbon fibre composite is molded and glues the integrated device and method of riveting with metal sheet |
| CN113167217A (en) * | 2018-12-19 | 2021-07-23 | 通用电气公司 | Joined rotor blades having internal support structures with different fiber orientations for pin reinforcement |
| CN114953514A (en) * | 2021-02-19 | 2022-08-30 | 河北雷萨重型工程机械有限责任公司 | Crane, auxiliary crane boom thereof, boom cylinder of auxiliary crane boom and manufacturing method of boom cylinder |
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| WO2009031657A1 (en) * | 2007-09-07 | 2009-03-12 | Toyota Jidosha Kabushiki Kaisha | Laminated structure for prepreg |
| CN104169077A (en) * | 2012-02-08 | 2014-11-26 | 奎德兰特塑料合成股份公司 | Sheetlike composite material |
| CN104228087A (en) * | 2014-09-01 | 2014-12-24 | 机械科学研究总院先进制造技术研究中心 | Method for preparing composite material prepreg |
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| EP1342544B1 (en) * | 2002-03-08 | 2008-03-12 | Gurit (UK) Limited | Moulding material |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108297458A (en) * | 2018-04-04 | 2018-07-20 | 吉林大学 | Carbon fibre composite is molded and glues the integrated device and method of riveting with metal sheet |
| CN108297458B (en) * | 2018-04-04 | 2023-05-02 | 吉林大学 | Forming and riveting method for carbon fiber composite material and metal plate |
| CN113167217A (en) * | 2018-12-19 | 2021-07-23 | 通用电气公司 | Joined rotor blades having internal support structures with different fiber orientations for pin reinforcement |
| CN113167217B (en) * | 2018-12-19 | 2024-06-07 | Lm风力发电公司 | Bonded rotor blade with internal support structure having different fiber orientations for pin reinforcement |
| CN114953514A (en) * | 2021-02-19 | 2022-08-30 | 河北雷萨重型工程机械有限责任公司 | Crane, auxiliary crane boom thereof, boom cylinder of auxiliary crane boom and manufacturing method of boom cylinder |
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Application publication date: 20161012 |