CN102390129B - Foam interlayer structure compound material and preparation method thereof - Google Patents
Foam interlayer structure compound material and preparation method thereof Download PDFInfo
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- CN102390129B CN102390129B CN201110241089.7A CN201110241089A CN102390129B CN 102390129 B CN102390129 B CN 102390129B CN 201110241089 A CN201110241089 A CN 201110241089A CN 102390129 B CN102390129 B CN 102390129B
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- 239000006260 foam Substances 0.000 title claims abstract description 60
- 239000000463 material Substances 0.000 title claims abstract description 23
- 150000001875 compounds Chemical class 0.000 title claims abstract description 18
- 239000011229 interlayer Substances 0.000 title claims abstract description 17
- 238000002360 preparation method Methods 0.000 title claims abstract description 10
- 239000011162 core material Substances 0.000 claims abstract description 39
- 239000002131 composite material Substances 0.000 claims description 17
- 238000000034 method Methods 0.000 claims description 15
- 241000209094 Oryza Species 0.000 claims description 8
- 235000007164 Oryza sativa Nutrition 0.000 claims description 8
- 235000009566 rice Nutrition 0.000 claims description 8
- 238000007711 solidification Methods 0.000 claims description 8
- 230000008023 solidification Effects 0.000 claims description 8
- 239000011347 resin Substances 0.000 claims description 7
- 229920005989 resin Polymers 0.000 claims description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- 239000003365 glass fiber Substances 0.000 claims description 4
- 239000007943 implant Substances 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 2
- 239000004697 Polyetherimide Substances 0.000 claims description 2
- 229920002873 Polyethylenimine Polymers 0.000 claims description 2
- 239000004642 Polyimide Substances 0.000 claims description 2
- 239000004793 Polystyrene Substances 0.000 claims description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 2
- 229920001601 polyetherimide Polymers 0.000 claims description 2
- 229920001721 polyimide Polymers 0.000 claims description 2
- 229920002223 polystyrene Polymers 0.000 claims description 2
- 239000004814 polyurethane Substances 0.000 claims description 2
- 229920002635 polyurethane Polymers 0.000 claims description 2
- 229920000915 polyvinyl chloride Polymers 0.000 claims description 2
- 239000004800 polyvinyl chloride Substances 0.000 claims description 2
- 239000010936 titanium Substances 0.000 claims description 2
- 229910052719 titanium Inorganic materials 0.000 claims description 2
- 238000010008 shearing Methods 0.000 abstract description 7
- 239000011159 matrix material Substances 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 6
- 238000010276 construction Methods 0.000 description 5
- 230000002708 enhancing effect Effects 0.000 description 5
- 239000010410 layer Substances 0.000 description 5
- 238000005452 bending Methods 0.000 description 4
- 230000006835 compression Effects 0.000 description 4
- 238000007906 compression Methods 0.000 description 4
- 238000009958 sewing Methods 0.000 description 4
- 239000004593 Epoxy Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 239000004744 fabric Substances 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 239000002356 single layer Substances 0.000 description 3
- 230000006378 damage Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000005187 foaming Methods 0.000 description 2
- 238000002513 implantation Methods 0.000 description 2
- 239000012528 membrane Substances 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 229920000784 Nomex Polymers 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000032798 delamination Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000004763 nomex Substances 0.000 description 1
- 239000012779 reinforcing material Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
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Abstract
The invention discloses a foam interlayer structure compound material and a preparation method thereof. A foam core material in the compound material is arranged between an upper skin and a lower skin, wherein one ends of one group of pultrusion rods in the foam core material are connected with the upper skin, the other ends of the group of pultrusion rods are connected with the lower skin to form a *-shaped structure, and pultrusion rods for connecting the upper skin and the lower skin are arranged between every two adjacent *-shaped structures. In the interlayer structure compound material, a plurality of pins are arranged in a foam matrix to form a space grid structure, thus the bonding force between the skins and the core material is improved, and because of geometrical features of the grid structure, the performances such as shearing resisting rigidity can be greatly improved. The foam interlayer structure compound material can be applied to aircraft members with high rigidity and weight requirements, such as wallboards, wing surfaces, tail beams and other main load-carrying structures.
Description
Technical field
The present invention relates to a kind of foamed composite, specifically a kind of foam interlayer structure compound material and preparation method thereof.
Background technology
The composite sandwich plate that closed pore rigid foam is made core has good dimensional stability in the situation of being heated, and has good resistance to chemical corrosion, thereby is widely used in the fields such as Aeronautics and Astronautics and navigation.The major defect of closed pore rigid foam be its Rigidity and strength all than comb core low (comprising NOMEX papery honeycomb), therefore with it, making composite sandwich plate stretching, compression, shearing and bending strength and the rigidity of core all will be lower than the honeycomb sandwich panel of identical core density.Owing to laterally not strengthening, panel and core are easy to occur unsticking and destroy simultaneously, and particularly, under impact loading, panel and core are easy to occur unsticking and layering, and then cause catastrophic consequence.These drawbacks limit foam layer material be used on Aircraft Main load-carrying construction, such as key positions such as fuselage and wings.A kind of effectively horizontal enhancing technology of visible development is very necessary.
Above-mentioned shortcoming based on foamed sandwich structure, foreign scholar has proposed many methods to strengthen the performance of its through-thickness, wherein especially with sewing and Z-Pin, strengthens the most representative.Large quantity research shows that sewing can improve the ability of foamed sandwich structure opposing delamination failure significantly, particularly can effectively stop the I type fracture of sandwich plate.But stitching process exists the defect of self: sewing enhancing technology can form resin-rich area near surface, two ends near suture pin hole, the existence of this resin-rich area, can cause laminate surface resin content too high, the easy moisture absorption in surface also produces micro-crack, becomes the initial damage source of destruction.In addition, sewing can increase plate thickness, makes panel fiber content step-down, reduces the Rigidity and strength of laminate.For these reasons, Z-Pin enhancing technology became in recent years the focus of research both at home and abroad.
Z-Pin enhancing technology is that fibrous composite pultrusion rod (being Pin) is implanted to formation of foam three-dimensional truss core material structure at a certain angle, embeds covering form mechanical connection at solidification process ZhongPin two ends.Z-Pin sandwich has following outstanding advantages: the direct Pin co-curing with embedding covering of composite material skin of (1) sandwich, without glued membrane, not only simplified technique but also improved intensity and reduced weight; (2) three-dimensional truss that Pin forms has very high structure efficiency; (3) angle and the density due to Pin all can design, and sandwich has larger design freedom, realizes local high-mechanic.
What the application of Z-Pin enhancing technology was maximum is X-cor sandwich, although X-cor sandwich has a lot of advantages, rigidity and weight is being required to use and can have insufficient strength, the caducous deficiency in core and top layer in high aircraft component.
Summary of the invention
For the deficiencies in the prior art, the object of this invention is to provide a kind of foam interlayer structure compound material and preparation method thereof, this foam sandwich construction composite has the characteristics such as light, the high peeling resistance of quality and plate face normal strength height, can be applicable to rigidity and weight to require high aircraft component, as wallboard, aerofoil, tail boom and other main force support structure etc.
The object of the invention is to be achieved through the following technical solutions:
, it is characterized in that: this composite comprises covering, lower covering, foam core material and pultrusion rod, foam core material is arranged between covering and lower covering; The one end that is arranged on one group of pultrusion rod in foam core material is connected with upper covering, and the other end is connected with lower covering and forms rice font structure, and between adjacent two meters of font structures, is provided with the pultrusion rod that connects upper covering and lower covering.
Pultrusion rod of the present invention is a kind of in carbon fiber pin, glass fibre pin, titanium pin, aluminium alloy pin or stainless pin, and diameter is 0.2-0.9mm.Described carbon fiber pin, glass fibre pin solidify after resin prepreg, and the volume content of resin is at 40-60%.Described pultrusion rod end is sharpening shape.Described pultrusion rod two ends in solidification process embed covering and lower covering is mechanical connection.Described foam core material is a kind of in polyurethane, polystyrene, polyvinyl chloride, polyimides, PEI or Polymethacrylimide material.
An its preparation method for foam interlayer structure compound material, is characterized in that this preparation method comprises following operation:
1) by foam core material excision forming;
2) pultrusion rod is become rice font implant in foam core material, the pultrusion rod of vertical layout is set between adjacent two meters of font structures, and the two ends of pultrusion rod are stretched out outside foam core material;
3) covering on foam core material upside is laid, covering under foam core material downside is laid;
4) adopt vacuum bag cure technological forming, obtain foam interlayer structure compound material.
In the present invention, the pin(pultrusion rod in composite) connect and support upper and lower covering, this pultrusion rod structure is communicated with reinforcing material and the matrix of upper and lower panel, and moulding in same technical process and form an integral body does not have interface without glued membrane.In this sandwich material, countless pin are placed in foam base plate and form space grid structure, have not only improved the adhesion of covering and core, and due to the geometrical property of grid structure, can increase substantially the performances such as anti-shearing rigidity.Composite of the present invention has the characteristics such as light, the high peeling resistance of quality and plate face normal strength height, can be applicable to rigidity and weight to require high aircraft component, as wallboard, aerofoil, tail boom and other main force support structure etc.
Pin of the present invention adopts and mixes arrangement mode implantation foam core material, in this sandwich material, countless pin are placed in foam base plate and form space net rack rice font structure, not only improved the adhesion of covering and core, and due to the geometrical property of grid structure, can increase substantially the performances such as anti-shearing rigidity.Can be applicable to rigidity and weight to require high aircraft component, as wallboard, aerofoil, tail boom and other main force support structure etc.
In the present invention, rice font structure is implanted the X-type structure of foam section with single angle than pin, have more excellent mechanical strength, has widened the range of application of sandwich foaming structure composite.For sandwich foaming structure composite research and performance improvement provide Liao Xin path.
Accompanying drawing explanation
Fig. 1 is the structural representation of foam interlayer structure compound material of the present invention.
Fig. 2 is covering vacuum solidification process curve figure.
The specific embodiment
Embodiment 1
, see Fig. 1, this composite comprises covering 1, lower covering 2, foam core material 3 and pultrusion rod 4, foam core material 3 is arranged on 2, covering 1 and lower covering; The one end that is arranged on one group of pultrusion rod 4 in foam core material 3 is connected with upper covering 1, and the other end is connected with lower covering 2 and forms rice font structure, and between adjacent two meters of font structures, is provided with the pultrusion rod 4 that connects upper covering 1 and lower covering 2.
An its preparation method for foam interlayer structure compound material, comprises following operation:
It is 50kg/m that core is selected density
3polymethacrylimide foam, on special tooling, pin is implanted to foam core material with the hybrid mode perpendicular to foam surface and certain angle and form rice font structure, implantation density perpendicular to foam surface pin is 5mm * 5mm, certain angle pin adopts and becomes the mode of 45o with foam surface, implants density 10mm * 10mm.It is the glass-epoxy Fabric prereg of 0.15 mm that upper and lower covering adopts thickness in monolayer, adopts 3 layers of laying.Require pin to want embedding people ground floor laying, guarantee the good combination of pin and laying.Adopt vacuum solidification technique, curing process curve is as Fig. 2.After solidifying cooling, obtain a meter font structure foam sandwich construction composite, the principle placed in the middle, symmetrical according to pin, specimen size is chosen as follows: concora crush sample is 60mm * 65mm; Shearing sample is 60 mm * 285mm; Bend specimen is 60 mm * 285mm.
Compression modulus 238.8MPa after tested; Shear strength 29.88MPa; Bending strength 456Mpa.
It is 50kg/m that core is selected density
3polymethacrylimide foam, pin is become to the mode of 45o on special tooling with foam surface, implant density 10mm * 10mm.It is the glass-epoxy Fabric prereg of 0.15 mm that upper and lower covering adopts thickness in monolayer, adopts 3 layers of laying.Require pin to want embedding people ground floor laying, guarantee the good combination of pin and laying.Adopt vacuum solidification technique, curing process curve is as Fig. 2.After solidifying cooling, obtain a meter font foam sandwich construction composite, the principle placed in the middle, symmetrical according to pin, specimen size is chosen as follows: concora crush sample is 60mm * 65mm; Shearing sample is 60 mm * 285mm; Bend specimen is 60 mm * 285mm.
Compression modulus 65.6MPa after tested; Shear strength 6.87MPa; Bending strength 255Mpa.
Comparative example 1
It is 50kg/m that core is selected density
3polymethacrylimide foam, without pin, strengthen, it is the glass-epoxy Fabric prereg of 0.15 mm that upper and lower covering adopts thickness in monolayer, adopts 3 layers of laying.Require pin to want embedding people ground floor laying, guarantee the good combination of pin and laying.Adopt vacuum solidification technique, curing process curve is as Fig. 2.After solidifying cooling, obtain foam sandwich construction composite, specimen size is chosen as follows: concora crush sample is 60mm * 65mm; Shearing sample is 60 mm * 285 mm; Bend specimen is 60mm * 285mm.
Compression modulus 18.9MPa after tested; Shear strength 2.34MPa; Bending strength 45Mpa.
Known by above-mentioned experiment contrast: composite of the present invention has the characteristics such as light, the high peeling resistance of quality and plate face normal strength height, can be applicable to rigidity and weight to require high aircraft component, as wallboard, aerofoil, tail boom and other main force support structure etc.
Claims (5)
1. a foam interlayer structure compound material, is characterized in that: this composite comprises covering (1), lower covering (2), foam core material (3) and pultrusion rod (4), and foam core material (3) is arranged between covering (1) and lower covering (2); The one end that is arranged on the one group of pultrusion rod (4) in foam core material (3) is connected with upper covering (1), the other end is connected with lower covering (2) and forms rice font structure, and between adjacent two meters of font structures, is provided with the pultrusion rod (4) that connects upper covering (1) and lower covering (2); Described pultrusion rod (4) end is sharpening shape; Described pultrusion rod (4) two ends in solidification process embed covering (1) and lower covering (2) is mechanical connection.
2. foam interlayer structure compound material according to claim 1, is characterized in that: a kind of in carbon fiber pin, glass fibre pin, titanium pin, aluminium alloy pin or stainless pin of described pultrusion rod (4), diameter is 0.2-0.9mm.
3. foam interlayer structure compound material according to claim 2, is characterized in that: described carbon fiber pin, glass fibre pin solidify after resin prepreg, and the volume content of resin is at 40-60%.
4. foam interlayer structure compound material according to claim 1, is characterized in that: described foam core material is a kind of in polyurethane, polystyrene, polyvinyl chloride, polyimides, PEI or Polymethacrylimide material.
5. an its preparation method for foam interlayer structure compound material claimed in claim 1, is characterized in that this preparation method comprises following operation:
1) by foam core material excision forming;
2) pultrusion rod is become rice font implant in foam core material, described pultrusion rod end is sharpening shape, the pultrusion rod of vertical layout is set between adjacent two meters of font structures, and the two ends of pultrusion rod is stretched out outside foam core material;
3) covering on foam core material upside is laid, covering under foam core material downside is laid; Described pultrusion rod two ends in solidification process embed covering and lower covering is mechanical connection;
(4) adopt vacuum bag cure technological forming, obtain foam interlayer structure compound material.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201110241089.7A CN102390129B (en) | 2011-08-22 | 2011-08-22 | Foam interlayer structure compound material and preparation method thereof |
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| CN201110241089.7A CN102390129B (en) | 2011-08-22 | 2011-08-22 | Foam interlayer structure compound material and preparation method thereof |
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| CN102390129B true CN102390129B (en) | 2014-01-15 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103144361A (en) * | 2013-04-01 | 2013-06-12 | 浙江联洋复合材料有限公司 | Sandwiched composite sheet and manufacturing method thereof |
| CN105196620A (en) * | 2015-10-20 | 2015-12-30 | 南京航空航天大学 | Partially-enhanced X-cor foam core sandwich T-joint structure and molding method |
| CN105252861A (en) * | 2015-11-03 | 2016-01-20 | 无锡同春新能源科技有限公司 | Novel buoyancy material consisting of laminated wood-plastic foam board, PIN core material and foam board |
| CN114211830A (en) * | 2021-12-23 | 2022-03-22 | 中国人民解放军国防科技大学 | Large composite material thrust cylinder and preparation method thereof |
| CN114801265A (en) * | 2022-05-06 | 2022-07-29 | 天津工业大学 | Prepreg vacuum plate and manufacturing method thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6027798A (en) * | 1995-11-01 | 2000-02-22 | The Boeing Company | Pin-reinforced sandwich structure |
| CN101508190A (en) * | 2009-03-26 | 2009-08-19 | 北京航空航天大学 | Foam reinforced sandwich structure with fiber bundle and preparation method using sewing-thermal expansion curing molding |
-
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- 2011-08-22 CN CN201110241089.7A patent/CN102390129B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6027798A (en) * | 1995-11-01 | 2000-02-22 | The Boeing Company | Pin-reinforced sandwich structure |
| CN101508190A (en) * | 2009-03-26 | 2009-08-19 | 北京航空航天大学 | Foam reinforced sandwich structure with fiber bundle and preparation method using sewing-thermal expansion curing molding |
Non-Patent Citations (2)
| Title |
|---|
| 原永虎.玻璃纤维制备X-cor夹层结构及性能研究.《工程科技I辑》.2010,(第S2期), |
| 玻璃纤维制备X-cor夹层结构及性能研究;原永虎;《工程科技I辑》;20100919(第S2期);第3、10、12-27页 * |
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