CN111169053A - Forming method of three-dimensional reinforced composite material - Google Patents
Forming method of three-dimensional reinforced composite material Download PDFInfo
- Publication number
- CN111169053A CN111169053A CN201811328351.XA CN201811328351A CN111169053A CN 111169053 A CN111169053 A CN 111169053A CN 201811328351 A CN201811328351 A CN 201811328351A CN 111169053 A CN111169053 A CN 111169053A
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- carbon fiber
- preform
- pin member
- laminate
- composite material
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- 238000000034 method Methods 0.000 title claims abstract description 35
- 239000011208 reinforced composite material Substances 0.000 title abstract description 8
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 45
- 239000004917 carbon fiber Substances 0.000 claims abstract description 45
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 45
- 239000002131 composite material Substances 0.000 claims abstract description 19
- 238000002513 implantation Methods 0.000 claims abstract description 8
- 239000011159 matrix material Substances 0.000 claims abstract description 4
- 239000011347 resin Substances 0.000 claims abstract description 3
- 229920005989 resin Polymers 0.000 claims abstract description 3
- 239000002184 metal Substances 0.000 claims description 23
- 239000006260 foam Substances 0.000 claims description 11
- 239000000835 fiber Substances 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 229910052799 carbon Inorganic materials 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 238000000465 moulding Methods 0.000 claims 8
- 238000009958 sewing Methods 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000010410 layer Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000000805 composite resin Substances 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007943 implant Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 239000012466 permeate Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D7/00—Producing flat articles, e.g. films or sheets
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
Abstract
The invention provides a forming method of a three-dimensional reinforced composite material, which comprises the following steps: the method comprises the following steps: preparing a carbon fiber Z-pin member (1) and a laminated plate prefabricated body (2) of a carbon fiber reinforced resin matrix composite material; step two: -making a preformed hole (4) in the laminate pre-form (2); and a third step: a carbon fiber Z-pin member (1) is implanted in the preformed hole (4). The invention aims to provide a forming method of a three-dimensional reinforced composite material, which can reduce the damage to a prefabricated body of a composite material laminated plate, reduce the damage to the mechanical property and the strength of the laminated plate and realize the implantation of a carbon fiber Z-pin into a large-thickness composite material laminated plate.
Description
Technical Field
The invention relates to the technical field of composite materials, in particular to a forming method of a three-dimensional reinforced composite material.
Background
The composite material laminated plate has good bearing capacity and is widely applied. However, in practical application, the strength of the interlayer connection interface is far lower than that of the composite material, so the connection interface is easy to fail and fall off.
One of the existing solutions is to adopt a sewing technology, however, the reciprocating swing of a needle head in the preset sewing process of a composite material structural member by adopting the sewing technology inevitably causes initial damage and damage to continuous fibers and a matrix of the composite material, so that the mechanical properties of a laminated plate including rigidity and strength are all reduced, and if the sewing technology structural member is utilized in a damp and hot environment, water molecules in the surrounding environment can permeate into the structural member along a preset sewing line, so that the structural member fails prematurely under a cyclic load, thereby not only reducing the structural life and even bringing greater loss, but also having another defect of high requirement on equipment and high price, especially the prepreg of a large aircraft structural member cannot be directly sewn by adopting the existing technology, and the use of the sewing technology is limited in many aspects.
Disclosure of Invention
Aiming at the problems in the related art, the invention aims to provide a forming method of a three-dimensional reinforced composite material, which can implant carbon fiber Z-pin into a composite material laminated plate with large thickness, reduce the damage to a composite material laminated plate preform, reduce the damage to the mechanical property and strength of the laminated plate and has very important significance for improving the utilization efficiency of the composite material.
In order to achieve the above object, the present invention provides a method for forming a three-dimensional reinforced composite material.
A method of forming a three-dimensional reinforced composite, comprising: the method comprises the following steps: preparing a carbon fiber Z-pin member and a laminated plate prefabricated body of a carbon fiber reinforced resin matrix composite material; step two: making a preformed hole in the laminate preform; and a third step: a carbon fiber Z-pin member is implanted into the preformed hole.
According to one embodiment of the present invention, in step two, metal pins are inserted into the laminate preform using an ultrasonic vibration apparatus, and then the metal pins are pulled out to form the preform holes.
According to one embodiment of the invention, metal pins are inserted into and through the laminate pre-form.
According to one embodiment of the invention, the metal pins are inserted in a direction perpendicular to the laminate pre-form.
According to one embodiment of the invention, the metal needle is a steel needle.
According to one embodiment of the invention, in step three, the diameter of the preformed hole is the same as the diameter of the carbon fiber Z-pin member.
According to an embodiment of the present invention, before step three, the method further includes: and arranging a foam carrier on the laminated plate prefabricated body, implanting a carbon fiber Z-pin member into the foam carrier, and then performing the step three.
According to one embodiment of the invention, in step three, a carbon fiber Z-pin member is implanted into the preformed hole using an ultrasonic implantation method.
According to an embodiment of the present invention, in step three, the method further includes: the portions of the carbon fiber Z-pin members not implanted into the preform holes are removed, and then the surface of the laminate preform is trimmed.
According to one embodiment of the invention, the thickness of the laminate preform is greater than or equal to 15 mm.
The invention has the beneficial technical effects that:
the prefabricated holes are manufactured in the laminated plate prefabricated body, so that the carbon fiber Z-pin member can directly penetrate through the laminated plate prefabricated body, the carbon fiber Z-pin can be implanted into the composite material laminated plate with large thickness, the damage to the composite material laminated plate prefabricated body is reduced, the damage to the mechanical property and strength of the laminated plate is reduced, and the prefabricated holes have very important significance for improving the utilization efficiency of the composite material.
Drawings
FIG. 1 is a schematic flow diagram of an embodiment of a method of forming a three-dimensional reinforced composite;
FIG. 2 is a schematic view of a metal pin inserted laminate preform;
FIG. 3 is a schematic view of a preformed hole;
FIG. 4 is a schematic view of a carbon fiber Z-pin member implanted into a preformed hole;
fig. 5 is a schematic representation of a laminate preform surface after finishing.
Detailed Description
The present invention will now be described with reference to the accompanying drawings, it being understood that the embodiments of the invention described in the following specification and the examples shown in the drawings are illustrative and not restrictive in any way.
In one embodiment of the present invention, as shown in fig. 1, a method of forming a three-dimensional reinforced composite material includes the following steps.
The method comprises the following steps: a carbon fiber Z-pin member 1 and a carbon fiber reinforced resin-based composite material laminate preform 2 are prepared.
In particular, the carbon fiber Z-pin member 1 may be prepared by a pultrusion process. At the same time the end of the carbon fiber Z-pin member 1 is provided with a sharp shape to facilitate the following implantation operation.
Step two: prefabricated holes 4 are made in the laminate preform 2.
Specifically, the positions of the holes are planned on the laminate preform 2. The density of the preformed holes 4 should not be too high, otherwise the laminate preform 2 would be damaged. The position of the preformed hole 4 is optimally designed according to the area of the laminate preform 2, the manufacturing material, and the like. Then, a prefabricated hole 4 is made in the laminate preform 2, the prefabricated hole 4 being as shown in fig. 3.
Step three: a carbon fibre Z-pin member 1 is implanted in the preformed hole 4.
Specifically, the length of the carbon fiber Z-pin member 1 is larger than or equal to the depth of the prefabricated hole 4, so that the carbon fiber Z-pin member 1 can penetrate through the laminated plate prefabricated body 2, the contact area between the carbon fiber Z-pin member 1 and the laminated plate prefabricated body 2 is increased, and the whole structural strength of the laminated plate prefabricated body 2 is enhanced.
As shown in fig. 2, in one embodiment, the preformed hole 4 in step two is manufactured by: the metal pins 3 are inserted into the laminate preform 2 using an ultrasonic vibration apparatus, and then the metal pins 3 are pulled out to form the preform holes 4. In this embodiment, the metal pins 3 should be inserted and pulled out as fast as possible, and cannot be shaken during the insertion and pulling out process, so as to avoid the metal pins 3 from damaging the laminated plate preform 2.
In one embodiment, metal pins 3 are inserted into and through the laminate panel preform 2. In this embodiment, the metal pins 3 are inserted into and penetrate the laminated board preform 2, and the preformed holes 4 are formed to penetrate the laminated board preform 2. The contact area of the carbon fiber Z-pin members 1 with the laminate preform 2 is increased, contributing to enhancement of the overall performance of the laminate preform 2.
In one embodiment, the metal pins 3 are inserted in a direction perpendicular to the laminate board preform 2. In the present embodiment, the metal pins 3 are inserted in the direction perpendicular to the laminate sheet preform 2, which reduces damage to the laminate sheet preform 2.
In one embodiment, the metal needle 3 is a steel needle. The steel needle has high hardness and rigidity, which is beneficial to manufacturing the prefabricated hole 4.
In one embodiment the diameter of the preformed hole 4 is the same as the diameter of the carbon fibre Z-pin member 1. In the present embodiment, the diameter of the preformed hole 4 is the same as the diameter of the carbon fiber Z-pin member 1, that is, the diameter of the metal needle 3 is also the same as the diameter of the carbon fiber Z-pin member 1. The same diameter is set, so that the resistance of the carbon fiber Z-pin member 1 in the implantation process can be reduced, and the carbon fiber Z-pin member 1 can be prevented from slipping off from the prefabricated hole 4.
In one embodiment, step three is preceded by the following steps: a foam carrier is provided on the laminate panel preform 2, and the carbon fiber Z-pin members 1 are implanted into the foam carrier, and then step three is performed. In an embodiment the foam carrier serves as a guide when the carbon fiber Z-pin member 1 is implanted, and therefore the foam carrier should be selected to have a certain stiffness of the foam. Of course, the foam carrier can be provided with 1 layer or more than 1 layer according to actual conditions.
In one embodiment, in step three, carbon fiber Z-pin member 1 is implanted into preformed hole 4 using an ultrasonic implantation method.
In one embodiment, step three further comprises: the portions of the carbon fiber Z-pin members 1 not implanted into the preform holes 4 are removed, and then the surface of the laminate preform 2 is trimmed. As shown in fig. 4, in the present embodiment, the length of the carbon fiber Z-pin member 1 is greater than or equal to the thickness of the laminate sheet preform 2, and therefore, there is a portion of the carbon fiber Z-pin member 1 that is not implanted into the preform hole 4. The surface of the laminate preform 2 is trimmed to ensure that the surface of the laminate preform 2 is flat. The trimmed laminate preform 2 is shown in fig. 5.
In one embodiment, the laminate preform 2 has a thickness greater than or equal to 15 mm. In the present embodiment, the thickness of the laminate preform 2 may be, for example, 15mm, 20mm, 25mm, or the like.
In yet another embodiment, the thickness of the laminate preform is 15mm, and the following is the step in this embodiment.
The method comprises the following steps: carbon fiber Z-pin members 1 and a laminate preform 15mm thick were prepared.
Step two: planning an implantation position of a carbon fiber Z-pin member 1 on a 15mm laminated plate prefabricated body; then, a metal needle 3 having the same diameter as that of the carbon fiber Z-pin member 1 is implanted into the 15mm laminate preform by using an ultrasonic vibration apparatus, and the metal needle 3 is pulled out to form a preform hole 4 into which the carbon fiber Z-pin member 1 is to be implanted.
Step three: arranging the carbon fiber Z-pin member 1 implanted into the foam preform on the 15mm laminate preform, and implanting the carbon fiber Z-pin member 1 into the preform hole 4 by using an ultrasonic implantation technique; finally, the part of the carbon fiber Z-pin member 1 not implanted into the prefabricated hole 4 is removed, and the surface of the 15mm laminate preform is trimmed.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A method of forming a three-dimensional reinforced composite, comprising:
the method comprises the following steps: preparing a carbon fiber Z-pin member (1) and a laminated plate prefabricated body (2) of a carbon fiber reinforced resin matrix composite material;
step two: -making a preformed hole (4) in the laminate pre-form (2); and
step three: -implanting the carbon fiber Z-pin member (1) into the preformed hole (4).
2. The molding method according to claim 1, wherein in the second step, a metal pin (3) is inserted into the laminate preform (2) using an ultrasonic vibration device, and then the metal pin (3) is pulled out to form the preform hole (4).
3. The molding method according to claim 2, wherein the metal needle (3) is inserted into and penetrates the laminate sheet preform (2).
4. The molding method according to claim 2, wherein the metal pin (3) is inserted in a direction perpendicular to the laminate sheet preform (2).
5. The forming method according to claim 2, characterized in that the metal needle (3) is a steel needle.
6. Moulding method according to claim 1, characterized in that in step three the diameter of the preformed hole (4) is the same as the diameter of the carbon fibre Z-pin member (1).
7. The molding method according to claim 1, further comprising, before said step three: arranging a foam carrier on the laminate pre-form (2) and implanting the carbon fiber Z-pin members (1) into the foam carrier, and then performing the third step.
8. Moulding method according to claim 1, characterized in that in step three the carbon fibre Z-pin member (1) is implanted into the preformed hole (4) using an ultrasonic implantation method.
9. The molding method according to claim 1, further comprising, in the third step: removing the part of the carbon fiber Z-pin member (1) not implanted into the prefabricated hole (4), and then finishing the surface of the laminate preform (2).
10. The molding method according to claim 1, wherein the thickness of the laminate sheet preform (2) is 15mm or more.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811328351.XA CN111169053A (en) | 2018-11-09 | 2018-11-09 | Forming method of three-dimensional reinforced composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811328351.XA CN111169053A (en) | 2018-11-09 | 2018-11-09 | Forming method of three-dimensional reinforced composite material |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111169053A true CN111169053A (en) | 2020-05-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811328351.XA Pending CN111169053A (en) | 2018-11-09 | 2018-11-09 | Forming method of three-dimensional reinforced composite material |
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| Country | Link |
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| CN (1) | CN111169053A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112297282A (en) * | 2020-09-29 | 2021-02-02 | 北京机科国创轻量化科学研究院有限公司 | Automatic Z-direction fiber implantation method for composite material preform |
| CN113677179A (en) * | 2021-09-28 | 2021-11-19 | 郑州佛光发电设备有限公司 | Electromagnetic shielding composite material and preparation method thereof |
| WO2023065911A1 (en) * | 2021-10-21 | 2023-04-27 | 南京玻璃纤维研究设计院有限公司 | Preform having preset hole channels having yarns implanted and preparation method for preform |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102107535A (en) * | 2010-12-22 | 2011-06-29 | 成都飞机工业（集团）有限责任公司 | Method for manufacturing carbon fiber reinforced resin matrix composite structure |
| CN103009638A (en) * | 2012-12-14 | 2013-04-03 | 航天神舟飞行器有限公司 | Interlaminar enhancement process for composite laminated plate for fuselage and airfoils of unmanned plane |
| CN105128366A (en) * | 2015-10-15 | 2015-12-09 | 南京航空航天大学 | Structure and method of reinforcing heat-conducting property of resin matrix composite with carbon fiber poles |
| CN106696118A (en) * | 2016-12-14 | 2017-05-24 | 中国航空工业集团公司基础技术研究院 | Z-direction enhancing method suitable for dry-state fiber preform |
| CN107009541A (en) * | 2017-06-13 | 2017-08-04 | 西北工业大学 | The ultrasonic method for implantation of composite Z-direction enhancing |
-
2018
- 2018-11-09 CN CN201811328351.XA patent/CN111169053A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102107535A (en) * | 2010-12-22 | 2011-06-29 | 成都飞机工业（集团）有限责任公司 | Method for manufacturing carbon fiber reinforced resin matrix composite structure |
| CN103009638A (en) * | 2012-12-14 | 2013-04-03 | 航天神舟飞行器有限公司 | Interlaminar enhancement process for composite laminated plate for fuselage and airfoils of unmanned plane |
| CN105128366A (en) * | 2015-10-15 | 2015-12-09 | 南京航空航天大学 | Structure and method of reinforcing heat-conducting property of resin matrix composite with carbon fiber poles |
| CN106696118A (en) * | 2016-12-14 | 2017-05-24 | 中国航空工业集团公司基础技术研究院 | Z-direction enhancing method suitable for dry-state fiber preform |
| CN107009541A (en) * | 2017-06-13 | 2017-08-04 | 西北工业大学 | The ultrasonic method for implantation of composite Z-direction enhancing |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112297282A (en) * | 2020-09-29 | 2021-02-02 | 北京机科国创轻量化科学研究院有限公司 | Automatic Z-direction fiber implantation method for composite material preform |
| CN112297282B (en) * | 2020-09-29 | 2022-08-05 | 北京机科国创轻量化科学研究院有限公司 | Automatic Z-direction fiber implantation method for composite material preform |
| CN113677179A (en) * | 2021-09-28 | 2021-11-19 | 郑州佛光发电设备有限公司 | Electromagnetic shielding composite material and preparation method thereof |
| WO2023065911A1 (en) * | 2021-10-21 | 2023-04-27 | 南京玻璃纤维研究设计院有限公司 | Preform having preset hole channels having yarns implanted and preparation method for preform |
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Application publication date: 20200519 |