CN219256657U - High-strength carbon fiber-preventing laminated composite board for deicing aircraft - Google Patents
High-strength carbon fiber-preventing laminated composite board for deicing aircraft Download PDFInfo
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- CN219256657U CN219256657U CN202223449008.5U CN202223449008U CN219256657U CN 219256657 U CN219256657 U CN 219256657U CN 202223449008 U CN202223449008 U CN 202223449008U CN 219256657 U CN219256657 U CN 219256657U
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- 239000002131 composite material Substances 0.000 title claims abstract description 60
- 229910052799 carbon Inorganic materials 0.000 title claims abstract description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims description 3
- 230000007246 mechanism Effects 0.000 claims abstract description 34
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 24
- 239000000758 substrate Substances 0.000 claims abstract description 23
- 238000010521 absorption reaction Methods 0.000 claims abstract description 17
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 13
- 239000004917 carbon fiber Substances 0.000 claims abstract description 13
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 13
- 238000004321 preservation Methods 0.000 claims abstract description 13
- 230000000694 effects Effects 0.000 claims abstract description 9
- 238000007731 hot pressing Methods 0.000 claims description 14
- 238000010438 heat treatment Methods 0.000 claims description 11
- 229910052751 metal Inorganic materials 0.000 claims description 10
- 239000002184 metal Substances 0.000 claims description 10
- 239000000843 powder Substances 0.000 claims description 9
- 238000005488 sandblasting Methods 0.000 claims description 8
- 239000004576 sand Substances 0.000 claims description 5
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- 239000002028 Biomass Substances 0.000 claims description 3
- 229920000742 Cotton Polymers 0.000 claims description 3
- 239000004169 Hydrogenated Poly-1-Decene Substances 0.000 claims description 3
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 235000019383 crystalline wax Nutrition 0.000 claims description 3
- 238000003475 lamination Methods 0.000 claims description 3
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 2
- 229910052710 silicon Inorganic materials 0.000 claims description 2
- 239000010703 silicon Substances 0.000 claims description 2
- 238000005265 energy consumption Methods 0.000 abstract description 7
- 238000009413 insulation Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 7
- 239000000463 material Substances 0.000 description 6
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 5
- 238000012546 transfer Methods 0.000 description 5
- 238000005728 strengthening Methods 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 238000003825 pressing Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005485 electric heating Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 230000032683 aging Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000020169 heat generation Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 239000000741 silica gel Substances 0.000 description 1
- 229910002027 silica gel Inorganic materials 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Laminated Bodies (AREA)
Abstract
The utility model relates to a high-strength carbon fiber preventing laminated composite board for aircraft deicing, which comprises a substrate, wherein the upper surface of the substrate is provided with a deicing mechanism for improving the heat conduction deicing effect of the substrate, the upper surface of the deicing mechanism is provided with a reinforcing mechanism for improving the strength of the composite board to adapt to high-altitude deicing, the deicing mechanism comprises a heat absorption layer fixed on the upper surface of the substrate, the upper surface of the heat absorption layer is fixedly provided with a first heat conduction layer, and the upper surface of the first heat conduction layer is fixedly provided with a heat insulation layer. This a fine stromatolite composite sheet of high strength anti-carbon for aircraft deicing has through setting up deicing mechanism, through mutually supporting between heat-absorbing layer, first heat-conducting layer, heat preservation and exothermic layer and the second heat-conducting layer etc. can utilize the heat-absorbing layer to adsorb the heat of loss in the aircraft operation and export the composite sheet outside along first heat-conducting plate etc. and carry out the intensification deicing, reduces deicing energy consumption to heat preservation etc. can delay heat loss extension deicing time.
Description
Technical Field
The utility model relates to the technical field of composite boards, in particular to a high-strength carbon fiber preventing laminated composite board for deicing an airplane.
Background
Icing of an aircraft is a phenomenon widely existing in flight practice, is one of important hidden dangers affecting flight safety and even causing catastrophic accidents, an ice control technology is an insurmountable key technology in aircraft development, and along with rapid development of application of composite materials in civil aviation, the consumption of the composite materials becomes one of important indexes of the modern civil aircraft advancement, the probability of encountering icing in flight is greatly improved, and effective safety protection under icing conditions is an important precondition of the safety, comfort and economy of the composite material civil aircraft.
The anti-icing deicing of the existing aircraft shell adopts a deicing method that an electric heating wire heating system is arranged under an existing aircraft composite material plate, and the existing electric heating deicing device is simply implemented and widely applied to the existing aircraft anti-icing/deicing system, but also has a plurality of problems, namely high power consumption, which is the most typical problem of a large aircraft, and causes great difficulty to the system design of the aircraft, for example, the power consumption of a 150-seat aircraft for deicing is up to 171KW, besides, the problems of reliability caused by unreasonable material matching and structural layout, such as poor interface binding force between a heating element and an insulating layer, fatigue aging of an outer skin, crack damage caused by thermal mismatch and the like, exist.
Disclosure of Invention
Aiming at the defects of the prior art, the utility model provides the high-strength carbon fiber preventing laminated composite board for aircraft deicing, which has the advantages of good deicing effect and the like, and solves the problem of high energy consumption in the existing aircraft deicing.
In order to achieve the above purpose, the present utility model provides the following technical solutions: the high-strength carbon fiber preventing laminated composite board for aircraft deicing comprises a substrate, wherein the upper surface of the substrate is provided with a deicing mechanism for improving the heat conduction deicing effect of the substrate, and the upper surface of the deicing mechanism is provided with a reinforcing mechanism for improving the strength of the composite board and adapting to high-altitude deicing;
the deicing mechanism comprises a heat absorption layer fixed on the upper surface of the substrate, a first heat conduction layer is fixed on the upper surface of the heat absorption layer, a heat preservation layer is fixed on the upper surface of the first heat conduction layer, a heat release layer is fixed on the upper surface of the heat preservation layer, and a second heat conduction layer is fixed on the upper surface of the heat release layer.
Further, a connecting plate is fixed on the lower surface of the substrate, and the thickness of the connecting plate is smaller than that of the substrate.
Further, the heat absorption layer is an organic heat absorption film layer, and the heat preservation layer is a heat preservation cotton layer.
Further, the first heat conduction layer is a heat conduction silicon sheet layer, and the second heat conduction layer is a heat conduction aluminum sheet layer.
Further, the exothermic layer is a biomass crystalline wax layer, and the thickness of the exothermic layer is two millimeters.
Further, the strengthening mechanism comprises a composite layer fixed on the upper surface of the second heat conduction layer, a hot pressing layer is fixed on the upper surface of the composite layer, a heating layer is fixed on the upper surface of the hot pressing layer, a strengthening layer is fixed on the upper surface of the heating layer, and a sand spraying layer is fixed on the upper surface of the strengthening layer.
Further, the composite layer is a composite metal powder lamination layer, and the hot pressing layer is a hot pressing metal sheet layer.
Further, the heating layer is a metal powder coating, the reinforcing layer is a composite material layer, and the sand-blasting layer is an alumina sand layer.
Compared with the prior art, the technical scheme of the application has the following beneficial effects:
1. this a fine stromatolite composite sheet of high strength anti-carbon for aircraft deicing has through setting up deicing mechanism, through mutually supporting between heat-absorbing layer, first heat-conducting layer, heat preservation and exothermic layer and the second heat-conducting layer etc. can utilize the heat-absorbing layer to adsorb the heat of loss in the aircraft operation and export the composite sheet outside along first heat-conducting plate etc. and carry out the intensification deicing, reduces deicing energy consumption to heat preservation etc. can delay heat loss extension deicing time.
2. This a high strength prevents carbon fiber stromatolite composite sheet for aircraft deicing has through having set up strengthening mechanism, mutually support between composite bed, layer, enhancement layer and sand-blasting layer and hot pressing layer etc. can utilize composite bed and enhancement layer and hot pressing layer to form multiple composite mechanism to strengthen composite sheet's bulk strength, and the layer that generates heat simultaneously can be convenient for heat transfer, avoids influencing heat absorption deicing efficiency.
Drawings
FIG. 1 is a schematic diagram of the structure of the present utility model;
FIG. 2 is a schematic diagram of a deicing mechanism according to the present utility model;
FIG. 3 is a schematic view of the reinforcement mechanism of the present utility model.
In the figure: 1 substrate, 2 deicing mechanisms, 201 heat absorption layer, 202 first heat conduction layer, 203 heat preservation layer, 204 heat release layer, 205 second heat conduction layer, 3 reinforcing mechanism, 301 composite layer, 302 hot pressing layer, 303 heat generation layer, 304 reinforcing layer, 305 sand spraying layer.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Embodiment one: referring to fig. 1, a high-strength carbon fiber preventing laminated composite board for aircraft deicing in this embodiment includes a substrate 1, a deicing mechanism 2 for improving a heat conduction deicing effect of the substrate 1 is disposed on an upper surface of the substrate 1, and a reinforcing mechanism 3 for improving strength of the composite board and adapting to high-altitude deicing is disposed on an upper surface of the deicing mechanism 2.
In this embodiment, a connection board is fixed on the lower surface of the substrate 1, and the thickness of the connection board is smaller than that of the substrate 1.
Embodiment two: referring to fig. 2, in order to reduce energy consumption and absorb dissipation heat for deicing an aircraft based on the first embodiment, the deicing mechanism 2 in this embodiment includes a heat absorbing layer 201 fixed on an upper surface of a substrate 1, the heat absorbing layer 201 is mainly attached to the substrate 1, heat generated and dissipated during operation of the aircraft is absorbed and collected by the substrate 1, and is used as deicing energy, a first heat conducting layer 202 is fixed on an upper surface of the heat absorbing layer 201, a heat insulating layer 203 is fixed on an upper surface of the first heat conducting layer 202, the heat insulating layer 203 can avoid rapid heat loss, delay heat loss and increase deicing time, an exothermic layer 204 is fixed on an upper surface of the heat insulating layer 203, the exothermic layer 204 is loaded into fine hollow spheres by loading melted and condensed exothermic materials to form uniform and fine solid powder, thereby realizing high-temperature and low-temperature exothermic effects, and a second heat conducting layer 205 is fixed on an upper surface of the exothermic layer 204.
In this embodiment, the heat absorbing layer 201 is an organic heat absorbing film layer, the heat insulating layer 203 is a heat insulating cotton layer, the first heat conducting layer 202 is a heat conducting silica gel sheet layer, the first heat conducting layer 202 can disperse and guide the gathered heat into the heat insulating layer 203 to expand the deicing area for use, the second heat conducting layer 205 is a heat conducting aluminum sheet layer, the heat releasing layer 204 is a biomass crystalline wax layer, the thickness of the heat releasing layer 204 is two millimeters, and the second heat conducting layer 205 can absorb and transfer the heat in the heat conducting aluminum sheet layer to the reinforcing mechanism 3 to improve the surface temperature of the reinforcing mechanism to avoid icing, so that the deicing effect of reducing energy consumption is achieved.
Embodiment III: referring to fig. 3, in order to improve the strength of the composite board and ensure the safety of the composite board for deicing an aircraft, the reinforcing mechanism 3 in this embodiment includes a composite layer 301 fixed on the upper surface of the second heat conducting layer 205, a heat pressing layer 302 fixed on the upper surface of the composite layer 301, a heat generating layer 303 fixed on the upper surface of the heat pressing layer 302, a reinforcing layer 304 fixed on the upper surface of the heat generating layer 303, and a plurality of composite structures formed by using different material components of the composite layer 301, the reinforcing layer 304 and the heat pressing layer 302, and the reinforcing mechanism is matched with each other to improve the overall strength of the composite board so as to keep stable and safe flight during aircraft use, and a sand blasting layer 305 is fixed on the upper surface of the reinforcing layer 304.
In this embodiment, the composite layer 301 is a composite metal powder lamination layer, the hot pressing layer 302 is a hot pressing metal sheet layer, the heating layer 303 is a metal powder coating, the heating layer 303 can be convenient for being matched with the deicing mechanism 2 to conduct heat transfer, the utilization efficiency of airborne energy can be greatly improved, absorbed heat is transferred to the reinforcing layer 304 and the sandblasted layer 305 to improve the surface temperature thereof to prevent icing, the heat absorption deicing efficiency is prevented from being influenced, the reinforcing layer 304 is a composite material layer, the sandblasted layer 305 is an alumina sand layer, the sandblasted layer 305 can strengthen the binding force, and the internal stress is reduced.
The working principle of the embodiment is as follows:
(1) When deicing is carried out on aircraft deicing by reducing energy consumption and absorbing dissipation heat, the heat absorption layer 201 is mainly attached to the substrate 1, heat generated and dissipated during aircraft operation is absorbed and gathered by the substrate 1 and used as deicing energy, the gathered heat can be scattered and led into the heat insulation layer 203 by the first heat conduction layer 202 to expand deicing area, the heat insulation layer 203 can avoid rapid heat loss, delay heat loss and increase deicing time, the heat release layer 204 is used for loading melted heat absorption and condensation heat dissipation materials into fine hollow spheres to prepare uniform and fine solid powder, the effects of high-temperature heat absorption and low-temperature heat dissipation are achieved, and the second heat conduction layer 205 can absorb and transfer the heat in the heat absorption layer to the reinforcing mechanism 3 to improve the surface temperature of the heat absorption and dissipation materials to avoid icing, so that the effect of reducing energy consumption and deicing is achieved.
(2) When the composite board strength is improved to ensure safe use of the aircraft deicing, the composite layer 301, the reinforcing layer 304 and the hot-pressing layer 302 can be utilized to form various composite structures by utilizing different material components of the composite layer, the integral strength of the composite board is improved by mutual cooperation so that the aircraft deicing mechanism can keep stable and safe flight when in use, the heating layer 303 can be convenient to cooperate with the deicing mechanism 2 to conduct heat transfer, the composite metal powder can conduct heat, the utilization efficiency of the aircraft energy can be greatly improved, the adsorbed heat can be transferred to the reinforcing layer 304 and the sand blasting layer 305 to improve the surface temperature of the reinforcing layer 304 and the sand blasting layer 305 to prevent icing, the heat absorption deicing efficiency is prevented from being influenced, the sand blasting layer 305 can strengthen the binding force and reduce the use of internal stress.
It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. High-strength carbon fiber-preventing laminated composite board for deicing aircraft, comprising a base board (1), and is characterized in that: the upper surface of the substrate (1) is provided with a deicing mechanism (2) for improving the heat conduction deicing effect of the substrate (1), and the upper surface of the deicing mechanism (2) is provided with a reinforcing mechanism (3) for improving the strength of the composite board and adapting to high-altitude deicing;
deicing mechanism (2) are including fixing heat-absorbing layer (201) at base plate (1) upper surface, the upper surface of heat-absorbing layer (201) is fixed with first heat conduction layer (202), the upper surface of first heat conduction layer (202) is fixed with heat preservation (203), the upper surface of heat preservation (203) is fixed with exothermic layer (204), the upper surface of exothermic layer (204) is fixed with second heat conduction layer (205).
2. A high strength carbon fiber reinforced composite panel for deicing aircraft according to claim 1, wherein: the connecting plate is fixed on the lower surface of the base plate (1), and the thickness of the connecting plate is smaller than that of the base plate (1).
3. A high strength carbon fiber reinforced composite panel for deicing aircraft according to claim 1, wherein: the heat absorption layer (201) is an organic heat absorption film layer, and the heat preservation layer (203) is a heat preservation cotton layer.
4. A high strength carbon fiber reinforced composite panel for deicing aircraft according to claim 1, wherein: the first heat conduction layer (202) is a heat conduction silicon sheet layer, and the second heat conduction layer (205) is a heat conduction aluminum sheet layer.
5. A high strength carbon fiber reinforced composite panel for deicing aircraft according to claim 1, wherein: the heat release layer (204) is a biomass crystalline wax layer, and the thickness of the heat release layer (204) is two millimeters.
6. A high strength carbon fiber reinforced composite panel for deicing aircraft according to claim 1, wherein: the reinforcing mechanism (3) comprises a composite layer (301) fixed on the upper surface of the second heat conduction layer (205), a hot pressing layer (302) is fixed on the upper surface of the composite layer (301), a heating layer (303) is fixed on the upper surface of the hot pressing layer (302), a reinforcing layer (304) is fixed on the upper surface of the heating layer (303), and a sand blasting layer (305) is fixed on the upper surface of the reinforcing layer (304).
7. A high strength carbon fiber reinforced composite panel for deicing an aircraft according to claim 6, wherein: the composite layer (301) is a composite metal powder lamination layer, and the hot pressing layer (302) is a hot pressing metal sheet layer.
8. A high strength carbon fiber reinforced composite panel for deicing an aircraft according to claim 6, wherein: the heating layer (303) is a metal powder coating, the reinforcing layer (304) is a composite material layer, and the sand blasting layer (305) is an alumina sand layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223449008.5U CN219256657U (en) | 2022-12-23 | 2022-12-23 | High-strength carbon fiber-preventing laminated composite board for deicing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223449008.5U CN219256657U (en) | 2022-12-23 | 2022-12-23 | High-strength carbon fiber-preventing laminated composite board for deicing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219256657U true CN219256657U (en) | 2023-06-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223449008.5U Active CN219256657U (en) | 2022-12-23 | 2022-12-23 | High-strength carbon fiber-preventing laminated composite board for deicing aircraft |
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| Country | Link |
|---|---|
| CN (1) | CN219256657U (en) |
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2022
- 2022-12-23 CN CN202223449008.5U patent/CN219256657U/en active Active
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