CN104527173A - Composite damping layer toughened thin layer and preparation method thereof - Google Patents
Composite damping layer toughened thin layer and preparation method thereof Download PDFInfo
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- CN104527173A CN104527173A CN201410737444.3A CN201410737444A CN104527173A CN 104527173 A CN104527173 A CN 104527173A CN 201410737444 A CN201410737444 A CN 201410737444A CN 104527173 A CN104527173 A CN 104527173A
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- 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
- B32B5/022—Non-woven fabric
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- 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
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/12—Layered products comprising a layer of synthetic resin next to a fibrous or filamentary layer
-
- 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
- B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
-
- 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
- B32B37/14—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
- B32B37/15—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer being manufactured and immediately laminated before reaching its stable state, e.g. in which a layer is extruded and laminated while in semi-molten state
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- 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
- B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
- B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B9/047—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material made of fibres or filaments
-
- 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
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/02—Synthetic macromolecular fibres
-
- 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
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
Abstract
The invention relates to a composite damping layer toughened thin layer and a preparation method thereof. The invention discloses a preparation method for a novel interlayer toughened layer with a damping vibration attenuation function and an application technology of the interlayer toughened layer in continuous carbon fiber reinforced laminated composite materials. A low surface density non-woven fabric with a network structure, a porous film or textile is adopted as the functional carrier to load polyvinylidene fluoride PVDF, then the composite toughened thin layer is placed at the interlayer of a conventional carbon fiber laminated composite material by an intercalation technology to conduct moulding solidification, thus obtaining the structural damping composite material with the toughness enhanced by more than 3 times. The method is easy to operate, and the obtained composite material not only has significantly improved toughness, no obvious loss of static mechanical properties, obviously increased vibration attenuation rate, but also causes little composite material weight gain.
Description
Technical field
The present invention relates to functional composite material field, particularly relate to toughness reinforcing thin layer of a kind of composite damping layer and preparation method thereof and utilize the preparation of this damping layer to have high tenacity concurrently, the Structural Damping Composite of high strength.
Background technology
Advanced Resin-based Composites is with its high specific strength, and the Scalability of high ratio modulus and performance is in aviation, and space flight, building, the application in the fields such as chemical industry is increasingly extensive.In recent years along with aerospace flight vehicle is to high speed, lighting direction, plant equipment is to high speed, efficiently, automation direction development, the malicious influences of structure vibration and structure borne noise environment to the dynamics environment of precision electronic device and equipment constantly aggravates, reduce precision and the reliability of navigation and control system, need badly and carry out vibration and noise reducing to improve its mechanical environment to structure, extending structure bears the active time of cyclic loading and impact.Facts have proved that in structure, add damping material is suppress one of the most effective technological means of vibration & noise in recent years.Damping material is that one can absorb vibration mechanical energy, and a kind of functional material it being converted into heat energy, electric energy, magnetic energy or other forms of energy and losing.Structural damping material is the existing material retaining again the structure-function integration of fine strength and stiffness compared with high damping properties, if directly by the damping material for preparing and structural material compound use, be easy to cause structure to peel off, and the use of damping layer especially constrained damping structure easily cause declining to a great extent of overall structure Rigidity and strength.On the other hand, it is usually responsive to low velocity impact that continuous carbon fibre strengthens resin-based laminated construction composite, easy formation internal impact delamination damage, the compressive strength of composite is sharply reduced, the main method improving shock resistance delamination damage ability improves the interlaminar fracture toughness of composite, therefore, laminated construction composite toughness reinforcing is also the important research content of domestic and international aviation composite always.
At present, the method for composite material toughening is varied, as utilized more tough rubber or thermal plastic high polymer directly to carry out toughness reinforcing to thermoset substrate resin, but usually can bring the decline of heat resistance and rigidity thus, or the problem such as processing technology variation.A kind of method at laminated composite materials interlayer introducing ductile structure receives publicity, because maintaining shaping manufacturability and other mechanical property while its raising composite shock resistance vertical resolution, typical example Intercalation reaction independently the pure thermoplastic resin of high tenacity or thermosetting glue-line and " offing normal " toughening technology that grows up thereof (as Chinese patent CN101220561, CN101760965A), as inserted the thermoplastic film of porous.Also have and introduce resilient granules at interlayer, introduce rigidity intert structure and insert the technology etc. of high-tenacity fiber at interlayer at interlayer, as inserted nylon nonwoven fabrics, the fabric (namely utilizing the thin sheet fabric that thermoplastic resin fibre weaves) etc. of thermoplastic resin fibre all can make composite interlaminar fracture toughness increase substantially.
Summary of the invention
The present invention is in order to overcome the deficiency of above-mentioned technical problem, provide the toughness reinforcing thin layer of a kind of composite damping layer, by the supported on carriers polyvinylidene fluoride PVDF in porous, its objective is that the continuous carbon fibre preparing a kind of structure-function integration strengthens laminated resin based structures composite, this kind of material can take into account damping and amortization to alleviate structural vibration and height is toughness reinforcing to improve its impact injury tolerance limit.
The technical scheme solved the problems of the technologies described above is as follows:
The present invention first proposed preparation a kind of damping as intermediate state composite-toughness reinforcing bifunctional compound thin layer, and this thin layer is that the PVDF on carrier is formed by the carrier of areal density porous and uniform load.
Described carrier is the thin polymer film of the fabric of porous, the non-woven fabrics of porous or porous, and the thickness of carrier is 8-80 μm, and the surface density of carrier is 5g/m
2-40g/m
2.
Further, the non-woven fabrics of described porous is non woven cloth in polymer or non-polymer non-woven fabrics.
Further, described non woven cloth in polymer is one or more in nylon, PAEK, polyimides, PEI, polyether sulfone, polyether-ether-ketone, aramid fiber.
Further, described non-polymer non-woven fabrics is one or more in carbon fiber nonwoven fabric, carbon nano-tube non-woven fabrics, plant fiber non-woven fabric.
The invention allows for the preparation method of the toughness reinforcing thin layer of above-mentioned composite damping layer, comprise the following steps:
(1) PVDF is scattered in dimethyl formamide DMF or dimethylacetylamide DMAc and forms dispersion liquid, ensure that in dispersion liquid, PVDF content is 5%-30%;
(2) dispersion liquid of above-mentioned steps (1) gained is loaded on carrier;
(3) carrier of dispersion liquid is crossed in the load of dry above-mentioned steps (2) gained.
Further, in step (2), by dispersion liquid, the method loaded on carrier is: a) carrier floods or is sprayed on carrier by dispersion liquid in dispersion liquid; B) dispersion liquid is passed through carrier under negative pressure; C) brushing mode is adopted by homogeneous dispersion brushing at upper any one of carrier.
Technical solution of the present invention also proposed the application of the toughness reinforcing thin layer of above-mentioned composite damping layer, toughness reinforcing for this composite damping thin layer is placed on the interlayer of continuous carbon fibre laminated composite materials, after curing molding, make the high-toughness high-strength composite product with damping vibration attenuation.
Continuous carbon fibre is any one in T300, T800, T700, CCF300, and the weaving manner of continuous carbon fibre is any one in unidirectional, plain weave, twill or satin weave.
The matrix resin of continuous carbon fibre laminated composite materials is any one in epoxy resin, unsaturated polyester (UP), bimaleimide resin.
Curing molding is any one in autoclave molding, RTM, mold pressing, vacuum aided or vacuum-bag process.
The invention has the beneficial effects as follows:
The present invention has taken into account the high tenacity of continuous fiber laminated composite materials, high strength and damping vibration attenuation performance, its concrete technology of preparing is divided into preparation two step of the preparation of intermediate state material and the toughness reinforcing thin layer of composite damping and final state material and final high tenacity structure damp composite material, and its core technology is the toughness reinforcing thin layer of damping and complex technique thereof.The PVDF that the present invention is used and resin matrix have good binding ability, by load on loose structure can the basic distinctive high specific strength of holding structure composite and specific stiffness character constant, improve fracture toughness to more than 3 times simultaneously, improve the damping capacity of structure simultaneously.Because the Product Status of the composite according to the technology of the present invention design preparation remains common lamination prepreg and laminate state thereof, therefore in the occasion that conventional airplane composite can be applied, the toughness reinforcing damp composite material of height of the present invention all can be applied, and does not need to do any special change.
Accompanying drawing explanation
Below in conjunction with the drawings and specific embodiments, the present invention is further detailed explanation.
Fig. 1 is single cantilever beam vibration attenuation experimental provision schematic diagram;
Fig. 2 is the vibration attenuation figure of the Structural Damping Composite plate of different intercalation;
Fig. 3 is the SEM figure of the nylon nonwoven fabrics of load P VDF;
Fig. 4 is the SEM figure of the PEKC film of load P VDF;
Detailed description of the invention
Embodiment 1:
The implementation process of technical solution of the present invention is as follows:
1, PVDF is scattered in dimethyl formamide DMF or dimethylacetylamide DMAc and forms the dispersion liquid that concentration is 5-30%;
2, be 80 μm by thickness, surface density is 40g/m
2aramid fiber non-woven fabrics or thickness be 53 μm, surface density is 20g/m
2nylon nonwoven fabrics or thickness be 25 μm, surface density is 8g/m
2polyether-ether-ketone non-woven fabrics or thickness be 75 μm, surface density is 26g/m
2polyimide nonwoven fabric or thickness be 15 μm, surface density is 7g/m
2polyether sulfone non-woven fabrics or thickness be 30 μm, surface density is 16g/m
2aramid fiber non-woven fabrics be immersed in the dispersion liquid of the PVDF obtained in above-mentioned steps 1, draw and propose liquid level dry or dry, repetition above-mentioned steps is flooded once again, obtains the non woven cloth in polymer of uniform load PVDF;
3, the interlayer non woven cloth in polymer that above-mentioned load obtains being positioned over one by one the epoxy resin-matrix prepreg of the unidirectional enhancing of continuous carbon fibre carries out laying, carbon fiber T300,3K or T800,12K, epoxy resin 5228 (Beijing Research Inst. of Aeronautic Material's product) or epoxy resin QY9611 (Beijing Aviation manufacturing engineering research institute product), obtain after sizing intercalation load toughness reinforcing-composite preform of damping integration;
4, by the curing process that this epoxy prepreg specifies, by above-mentioned toughness reinforcing-composite preform of damping integration utilizes conventional mold pressing or autoclave method to carry out vacuum forming solidification, obtains the composite product of the toughness reinforcing damping integration of epoxy resin-matrix.
Being the vibration attenuation figure of different intercalation material in Fig. 2, can obviously finding out from figure, the vibration attenuation speed of multiple material plate can be improved by adding 7 layers of nylon nonwoven fabrics, and vibration attenuation speed can be increased further by load P VDF in nylon nonwoven fabrics.
Fig. 3 is the SEM figure of the nylon nonwoven fabrics of load P VDF, as can be seen from the figure, PVDF is uniformly dispersed in the carrier but is not filled up in the space of nylon completely, matrix resin still can form continuous structure through space, thus ensureing that the mechanical property of material is not significantly affected, the high tenacity of PVDF adds that nylon nonwoven fabrics forms Reinforced structure jointly.
The final composite that the toughness reinforcing thin layer of a kind of damping obtained by load in nylon nonwoven fabrics that the present embodiment obtains intercalation obtain is compared to the composite of non-intercalation, I mode Ⅱ fracture toughness improves more than 4 times, more than 2 times are improved than the scheme of existing only intercalation nylon nonwoven fabrics, II mode Ⅱ fracture toughness improves more than 3 times than the multiple material plate of non-intercalation, 20% is improved than the scheme of existing only intercalation nylon nonwoven fabrics, damping factor improves 130% than the multiple material plate of non-intercalation, the composites weightening finish caused is minimum, and only about 0.5%.
Embodiment 2:
The implementation process of technical solution of the present invention is as follows:
1, PVDF is scattered in dimethyl formamide DMF or dimethylacetylamide DMAc and forms the dispersion liquid that concentration is 5-30%;
2, be 14g/m by thickness about 20 μm, surface density
2pAEK porous membrane (porosity about 40%) or thickness be 8 μm, surface density is 6g/m
2polyimide porous film or thickness about 25 μm, surface density be 11g/m
2pEI porous membrane or thickness is about 15um, surface density is 9g/m
2polyether-ether-ketone porous membrane be impregnated in the dispersion liquid of the PVDF described in step 1, draw and propose liquid level drying, repeat above-mentioned steps and flood twice again, obtain the polymer porous membrane of uniform load PVDF;
3, the polymer porous membrane that above-mentioned load obtains is positioned over one by one the interlayer that continuous carbon fibre strengthens the fabric of satin weave or plain weave or unidirectional or more several weaving manner mixing and carries out laying, carbon fiber T700,12K, obtain after sizing intercalation load toughness reinforcing-damping one composite preform;
4, RTM technique is utilized, liquid epoxy 3266 resin (Beijing Research Inst. of Aeronautic Material's product) injected precast body and flood completely, then the technique specified according to epoxy resin carries out shaping and solidification, at this moment, polyaryletherketone film or poly (ether ether ketone) film are dissolved in 3266 resins in the curing process, phase-splitting phase reversal, form the 3266-PAEK of malleableize or 3266-polyether-ether-ketone graininess co-continuous malleableize structure, finally obtain the shaping epoxy resin-matrix of RTM toughness reinforcing-composite product of damping integration.Polyimide porous film and PEI porous membrane then do not dissolve, and form independently intercalation play toughening effect at interlayer, equally finally obtain the composite product of toughness reinforcing-damping integration.
Fig. 4 is the SEM figure of the polyaryletherketone film of load P VDF, and as can be seen from the figure, PVDF also can be uniformly dispersed at film surface, and polyaryletherketone film itself is then dissolved in composite material solidification process, phase-splitting form the Reinforced structure of co-continuous.
Obtain in the present embodiment wherein a kind of toughness reinforcing-composite of damping function integration is compared to the composite of non-intercalation, drum interlaminar fracture toughness improves 30%, II mode Ⅱ fracture toughness improves 120%, damping capacity improves 50%, the composites weightening finish caused is minimum, and only about 0.3%.
Embodiment 3:
The implementation process of technical solution of the present invention is as follows:
1, PVDF is scattered in dimethyl formamide DMF or dimethylacetylamide DMAc and forms the dispersion liquid that concentration is 5-30%;
2, by above-mentioned dispersion liquid, utilize and to be loaded to that thickness is 35 μm, surface density is 14g/m under negative pressure by the method for carrier
2rIPSTOP or thickness be 25 μm, surface density is 11g/m
2polyether-ether-ketone fabric or thickness be 45 μm, surface density is 18g/m
2polyimides fabric on;
3, the interlayer fabric of above-mentioned load P VDF being positioned over one by one the epoxy prepreg that continuous carbon fibre strengthens carries out laying, carbon fiber T800,12K or CCF300,3K, epoxy resin QY9611 (Beijing Aviation manufacturing engineering research institute product) or epoxy resin 5228 (Beijing Research Inst. of Aeronautic Material's product), obtain the composite preform of toughness reinforcing-damping;
4, by the curing process that this epoxy prepreg specifies, utilize autoclave method to carry out forming and hardening, obtain the composite product of toughness reinforcing-damping.
Embodiment 4:
The implementation process of technical solution of the present invention is as follows:
1, PVDF is scattered in dimethyl formamide DMF or dimethylacetylamide DMAc and forms the dispersion liquid that concentration is 5-30%;
2, thickness is 75 μm, surface density is 26g/m to utilize brushing method to load to above-mentioned PVDF dispersion liquid
2polyimide fiber non-woven fabrics or thickness be 28 μm, surface density is 11g/m
2carbon nano-fiber non-woven fabrics or thickness be 8 μm, surface density is 5g/m
2carbon nano-tube non-woven fabrics on, obtain the toughness reinforcing thin layer of damping;
3, the above-mentioned altogether damping thin layer that load obtains is positioned over carbon fibre fabric interlayer one by one and carries out laying, carbon fiber T300,3K, after sizing, obtain the composite preform conducted electricity;
4, RTM technique is utilized, liquid span is come phthalimide (BM work) resin 6421 (Beijing Research Inst. of Aeronautic Material's product) or liquid-state epoxy resin 3266 (Beijing Research Inst. of Aeronautic Material), the technological requirement shaping according to this resin RTM is injected, and then carry out forming and hardening by the technique of regulation, finally obtain fibre reinforced, compared with high damping and high toughness reinforcing bimaleimide resin base composite material goods or epoxy resin-base composite material goods.
The above is only preferred embodiment of the present invention, not does any pro forma restriction to the present invention, every according in technical spirit of the present invention to any simple modification, equivalent variations that above embodiment is done, all fall within protection scope of the present invention.
Claims (10)
1. the toughness reinforcing thin layer of composite damping layer, it is characterized in that, this thin layer is made up of the carrier of areal density porous and uniform load polyvinylidene fluoride PVDF on the carrier, described carrier is the thin polymer film of the fabric of porous, the non-woven fabrics of porous or porous, the thickness of carrier is 8-80 μm, and the surface density of carrier is 5g/m
2-40g/m
2.
2. the toughness reinforcing thin layer of a kind of composite damping layer according to claim 1, is characterized in that, the non-woven fabrics of described porous is non woven cloth in polymer or non-polymer non-woven fabrics.
3. the toughness reinforcing thin layer of a kind of composite damping layer according to claim 2, is characterized in that, described non woven cloth in polymer is one or more in nylon, PAEK, polyimides, PEI, polyether sulfone, polyether-ether-ketone, aramid fiber.
4. the toughness reinforcing thin layer of a kind of composite damping layer according to claim 2, is characterized in that, described non-polymer non-woven fabrics is one or more in carbon fiber nonwoven fabric, carbon nano-tube non-woven fabrics, plant fiber non-woven fabric.
5. a preparation method for the toughness reinforcing thin layer of composite damping layer as claimed in claim 1, is characterized in that, comprise the following steps:
(1) PVDF is scattered in dimethyl formamide DMF or dimethylacetylamide DMAc and forms dispersion liquid, ensure that in dispersion liquid, PVDF content is 5%-30%;
(2) dispersion liquid of above-mentioned steps (1) gained is loaded on carrier;
(3) carrier of dispersion liquid is crossed in the load of dry above-mentioned steps (2) gained.
6. the preparation method of the toughness reinforcing thin layer of composite damping layer according to claim 5, is characterized in that, in step (2), the method loaded to by dispersion liquid on carrier is: a) carrier floods or is sprayed on carrier by dispersion liquid in dispersion liquid; B) dispersion liquid is passed through carrier under negative pressure; C) brushing mode is adopted by homogeneous dispersion brushing at upper any one of carrier.
7. the application of the toughness reinforcing thin layer of composite damping layer as claimed in claim 1, it is characterized in that: the interlayer toughness reinforcing for this composite damping thin layer being placed on continuous carbon fibre laminated composite materials, after curing molding, make the high-toughness high-strength composite product with damping vibration attenuation.
8. the application of the toughness reinforcing thin layer of composite damping according to claim 7, is characterized in that: continuous carbon fibre is any one in T300, T800, T700, CCF300, and the weaving manner of continuous carbon fibre is any one in unidirectional, plain weave, twill or satin weave.
9. the application of the toughness reinforcing thin layer of composite damping according to claim 7, is characterized in that: the matrix resin of continuous carbon fibre laminated composite materials is any one in epoxy resin, unsaturated polyester (UP), bimaleimide resin.
10. the application of the toughness reinforcing thin layer of composite damping according to claim 7, is characterized in that: curing molding is any one in autoclave molding, RTM, mold pressing, vacuum aided or vacuum-bag process.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410737444.3A CN104527173A (en) | 2014-12-05 | 2014-12-05 | Composite damping layer toughened thin layer and preparation method thereof |
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|---|---|---|---|
| CN201410737444.3A CN104527173A (en) | 2014-12-05 | 2014-12-05 | Composite damping layer toughened thin layer and preparation method thereof |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106433036A (en) * | 2016-08-29 | 2017-02-22 | 天津大学 | Method for preparing PVDF modified three-dimensional braided carbon fiber structural damping composite material |
| CN107269750A (en) * | 2017-06-28 | 2017-10-20 | 江苏兆鋆新材料股份有限公司 | A kind of 3 D weaving damp composite material leaf spring and preparation method thereof |
| CN107653694A (en) * | 2017-08-31 | 2018-02-02 | 常州苏达欧包装材料有限公司 | A kind of composite damping material and preparation method thereof |
| US10272651B1 (en) | 2017-10-18 | 2019-04-30 | Industrial Technology Research Institute | Fiber composite and manufacturing method thereof |
| TWI670176B (en) * | 2017-10-18 | 2019-09-01 | 財團法人工業技術研究院 | Fiber composite and manufacturing method thereof |
| CN111873485A (en) * | 2020-07-16 | 2020-11-03 | 中国航空制造技术研究院 | Damping intercalation with microstructure on surface, preparation method and composite material part |
| US11027534B2 (en) | 2017-10-18 | 2021-06-08 | Industrial Technology Research Institute | Fiber composite material and manufacturing method thereof |
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| CN103963398A (en) * | 2014-04-29 | 2014-08-06 | 中国航空工业集团公司北京航空材料研究院 | Dual-functional toughening-damping intercalation material and product prepared from same |
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| US5526324A (en) * | 1995-08-16 | 1996-06-11 | Poiesis Research, Inc. | Acoustic absorption and damping material with piezoelectric energy dissipation |
| CN103342026A (en) * | 2013-06-26 | 2013-10-09 | 中简科技发展有限公司 | Preparation method of damping material with co-curing structure |
| CN103963398A (en) * | 2014-04-29 | 2014-08-06 | 中国航空工业集团公司北京航空材料研究院 | Dual-functional toughening-damping intercalation material and product prepared from same |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106433036A (en) * | 2016-08-29 | 2017-02-22 | 天津大学 | Method for preparing PVDF modified three-dimensional braided carbon fiber structural damping composite material |
| CN107269750A (en) * | 2017-06-28 | 2017-10-20 | 江苏兆鋆新材料股份有限公司 | A kind of 3 D weaving damp composite material leaf spring and preparation method thereof |
| CN107653694A (en) * | 2017-08-31 | 2018-02-02 | 常州苏达欧包装材料有限公司 | A kind of composite damping material and preparation method thereof |
| US10272651B1 (en) | 2017-10-18 | 2019-04-30 | Industrial Technology Research Institute | Fiber composite and manufacturing method thereof |
| TWI670176B (en) * | 2017-10-18 | 2019-09-01 | 財團法人工業技術研究院 | Fiber composite and manufacturing method thereof |
| US11027534B2 (en) | 2017-10-18 | 2021-06-08 | Industrial Technology Research Institute | Fiber composite material and manufacturing method thereof |
| CN111873485A (en) * | 2020-07-16 | 2020-11-03 | 中国航空制造技术研究院 | Damping intercalation with microstructure on surface, preparation method and composite material part |
| CN111873485B (en) * | 2020-07-16 | 2022-06-10 | 中国航空制造技术研究院 | Damping intercalation with microstructure on surface, preparation method and composite material part |
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