CN218966364U - Fireproof carbon fiber composite board for deicing aircraft - Google Patents
Fireproof carbon fiber composite board for deicing aircraft Download PDFInfo
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- CN218966364U CN218966364U CN202223449111.XU CN202223449111U CN218966364U CN 218966364 U CN218966364 U CN 218966364U CN 202223449111 U CN202223449111 U CN 202223449111U CN 218966364 U CN218966364 U CN 218966364U
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Abstract
The utility model relates to an anti-carbon fiber composite board for fireproof airplane deicing, which comprises a base layer, wherein a cold-resistant component is arranged on the upper surface of the base layer, a heat-conducting component is arranged on the lower surface of the base layer, the cold-resistant component comprises a first adhesive layer arranged on the upper surface of the base layer, an ultraviolet-proof layer is fixed on the upper surface of the first adhesive layer, a sound blocking layer is fixed on the upper surface of the ultraviolet-proof layer, a tensile layer is fixed on the upper surface of the sound blocking layer, and a cold-resistant layer is fixed on the upper surface of the tensile layer. This prevent carbon fiber composite sheet for aircraft deicing through setting up cold-resistant layer, has made the improvement on the material on cold-resistant layer, selects for use thermoplastic polyester elastomer, because thermoplastic polyester elastomer possesses good cold-resistant ability, and thermoplastic polyester elastomer's impact resistance under low temperature condition is also very excellent simultaneously, accords with aircraft high altitude flight's condition, can prevent effectively that this carbon fiber composite sheet from being frozen out when flying, has guaranteed aircraft flight's safety simultaneously.
Description
Technical Field
The utility model relates to the technical field of carbon fiber-preventing composite boards, in particular to a carbon fiber-preventing composite board for deicing a fireproof airplane.
Background
Along with the rapid development of the application of the composite material in civil aviation, the dosage of the composite material becomes one of important indexes of the advancement of modern civil aircrafts, the probability of encountering icing in the flight is greatly improved, the effective safety protection under icing conditions is an important precondition of the safety, comfort and economy of the composite material civil aircraft, the aircraft icing is a phenomenon widely existing in the flight practice, is one of important hidden dangers affecting the flight safety and even causing catastrophic accidents, and the ice prevention and removal technology is an insurmountable key technology in the development of aircrafts.
In the prior art, aircraft icing is a phenomenon widely existing in flight practice, is one of important hidden dangers affecting flight safety and even causing catastrophic accidents, and the current aircraft deicing mode is realized by a resistance wire heating deicing prevention method and improvement on the material of a composite board, but the composite board can realize the purpose of preventing and removing ice of an aircraft, but the aircraft often sails at a high altitude of tens of thousands of meters, so that the cold resistance of the composite board is poor, and the flight safety of the aircraft is affected.
Disclosure of Invention
Aiming at the defects of the prior art, the utility model provides the carbon fiber-resistant composite board for preventing the deicing of the airplane from being damaged, which has the advantage of good cold resistance, and solves the problems that the cold resistance of the composite board is poor and the flight safety of the airplane is affected.
In order to achieve the above purpose, the present utility model provides the following technical solutions: the carbon fiber-preventing composite board for preventing the fire and airplane deicing comprises a base layer, wherein a cold-resistant component is arranged on the upper surface of the base layer, and a heat-conducting component is arranged on the lower surface of the base layer;
the cold-resistant assembly comprises a first adhesive layer arranged on the upper surface of a base layer, an ultraviolet-proof layer is fixed on the upper surface of the first adhesive layer, a sound blocking layer is fixed on the upper surface of the ultraviolet-proof layer, a tensile layer is fixed on the upper surface of the sound blocking layer, and a cold-resistant layer is fixed on the upper surface of the tensile layer.
Further, the first adhesive layer is a heat conducting pouring sealant layer, and the ultraviolet-proof layer is an acrylic coating.
Further, the sound blocking layer is a sound insulation damping glue layer, and the tensile layer is a polyester fiber coating.
Further, the cold-resistant layer is a thermoplastic polyester elastomer layer, and the thicknesses of the first adhesive layer, the ultraviolet-proof layer, the sound-blocking layer, the tensile layer and the cold-resistant layer are not more than two millimeters.
Further, the heat conduction assembly comprises a second adhesive layer arranged on the lower surface of the base layer, a flame retardant layer is fixed on the lower surface of the second adhesive layer, a compression resistant layer is fixed on the lower surface of the flame retardant layer, a first heat conduction layer is fixed on the lower surface of the compression resistant layer, and a second heat conduction layer is fixed on the lower surface of the first heat conduction layer.
Further, the second adhesive layer is a heat-conducting silica gel layer, and the flame-retardant layer is a polyvinyl chloride coating.
Further, the compression-resistant layer is a polypropylene coating, and the first heat-conducting layer is a graphene coating.
Further, the second heat conduction layer is a copper metal layer, and the thicknesses of the second adhesive layer, the flame retardant layer, the compression resistant layer, the first heat conduction layer and the second heat conduction layer are not more than two millimeters.
Compared with the prior art, the technical scheme of the application has the following beneficial effects:
1. this prevent fire prevention aircraft deicing with preventing carbon fiber composite sheet has set up cold-resistant subassembly in this prevent fire prevention aircraft deicing with preventing carbon fiber composite sheet, mutually supporting between each structure in cold-resistant subassembly, through setting up cold-resistant layer, has made the improvement on cold-resistant layer's material, selects for use thermoplastic polyester elastomer, because thermoplastic polyester elastomer possesses good cold-resistant ability, thermoplastic polyester elastomer's impact resistance under the low temperature condition is also very excellent simultaneously, accords with aircraft high altitude flight's condition, can prevent effectively that this prevent carbon fiber composite sheet from being frozen out when flying, guaranteed aircraft flight's safety simultaneously.
2. This prevent fire prevention aircraft deicing with preventing carbon fiber composite sheet has set up heat conduction subassembly in this prevent fire prevention aircraft deicing with preventing carbon fiber composite sheet, mutually support between each structure in the heat conduction subassembly, through setting up first heat conduction layer and second heat conduction layer, through the good heat conduction effect of first heat conduction layer and second heat conduction layer, can improve the utilization efficiency of airborne energy by a wide margin, reduce aircraft overall design's burden, can make the ice of preventing carbon fiber composite sheet outer knot can melt, guaranteed the security performance of aircraft.
Drawings
FIG. 1 is a schematic diagram of the structure of the present utility model;
FIG. 2 is a schematic view of a cold-resistant assembly of the present utility model;
fig. 3 is a schematic view of a heat conduction assembly according to the present utility model.
In the figure: 1 base layer, 2 cold-resistant components, 201 first adhesive layer, 202 ultraviolet-proof layer, 203 sound-blocking layer, 204 tensile layer, 205 cold-resistant layer, 3 heat-conducting components, 301 second adhesive layer, 302 flame-retardant layer, 303 compression-resistant layer, 304 first heat-conducting layer, 305 second heat-conducting 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, an anti-carbon fiber composite board for deicing a fireproof airplane in this embodiment includes a base layer 1, a cold-resistant component 2 is disposed on an upper surface of the base layer 1, and a heat-conducting component 3 is disposed on a lower surface of the base layer 1.
Embodiment two: referring to fig. 2, in order to effectively prevent the carbon fiber composite board from being frozen during flight, the cold-resistant component 2 in the embodiment includes a first adhesive layer 201 disposed on an upper surface of a base layer 1, an ultraviolet-proof layer 202 is fixed on an upper surface of the first adhesive layer 201, a sound blocking layer 203 is fixed on an upper surface of the ultraviolet-proof layer 202, a tensile layer 204 is fixed on an upper surface of the sound blocking layer 203, and a cold-resistant layer 205 is fixed on an upper surface of the tensile layer 204.
The first adhesive layer 201 is a heat-conducting pouring sealant, the first adhesive layer 201 is made of a heat-conducting pouring sealant material, the heat-conducting pouring sealant is a double-component condensation heat-conducting pouring sealant, sensitive circuits and components can be reliably protected for a long time in wide temperature and humidity changes, the heat-conducting pouring sealant has excellent electrical insulation performance, can resist environmental pollution, avoids damage to products caused by environmental factors such as stress, vibration and humidity, the ultraviolet-proof layer 202 is an acrylic coating, the ultraviolet-proof layer 202 is made of an acrylic material, and the weather resistance, the heat resistance and the ultraviolet resistance of the acrylic material are good, so that the heat-conducting pouring sealant can also adapt to the cracking deformation of a base surface to a certain extent.
The sound blocking layer 203 is a sound insulation damping glue layer, the sound insulation damping glue plays a key role in weakening and attenuating sound transmission, a good blocking effect can be achieved on sound, the tensile layer 204 is a polyester fiber coating, and the polyester fiber material has the greatest advantages of good wrinkle resistance and shape retention, high strength and elastic recovery capability, fastness and durability, and the tensile property of the carbon fiber-resistant composite board can be improved.
The cold-resistant layer 205 is a thermoplastic polyester elastomer layer, the thermoplastic polyester elastomer has good cold-resistant capability, meanwhile, the impact resistance of the thermoplastic polyester elastomer under the low temperature condition is very excellent, the aircraft high-altitude flight condition is met, the carbon fiber-resistant composite board can be effectively prevented from being frozen out during flight, the aircraft flight safety is ensured, and the thicknesses of the first adhesive layer 201, the ultraviolet-proof layer 202, the sound-resistant layer 203, the tensile layer 204 and the cold-resistant layer 205 are not more than two millimeters.
Embodiment III: referring to fig. 3, in order to greatly improve the utilization efficiency of the airborne energy and reduce the burden of the overall design of the aircraft on the basis of the first and second embodiments, the ice that is bound outside the carbon fiber-preventing composite board can be melted, and the safety performance of the aircraft is ensured, the heat conducting component 3 in this embodiment includes a second adhesive layer 301 disposed on the lower surface of the base layer 1, a flame retardant layer 302 is fixed on the lower surface of the second adhesive layer 301, a compression layer 303 is fixed on the lower surface of the flame retardant layer 302, a first heat conducting layer 304 is fixed on the lower surface of the compression layer 303, and a second heat conducting layer 305 is fixed on the lower surface of the first heat conducting layer 304.
The second adhesive layer 301 is a heat-conducting silica gel layer, the heat-conducting silica gel is a high-end heat-conducting compound, and the heat-conducting silica gel is not solidified, and the risk such as short circuit and the like can be avoided due to the non-conductive characteristic, the heat-conducting bonding sealing silica gel is a single-component heat-conducting type and room-temperature-curing organic silicon bonding sealing gel, the flame-retardant layer 302 is a polyvinyl chloride coating, the polyvinyl chloride material has good flame retardant performance, and the flame retardant performance of the carbon fiber-preventing composite board can be improved.
The compressive layer 303 is a polypropylene coating, and the polypropylene material has good compressive property, can improve the compressive property of the carbon fiber composite board, ensures the safety performance of an aircraft, and the first heat conducting layer 304 is a graphene coating.
The second heat conducting layer 305 is a copper metal layer, and the thicknesses of the second adhesive layer 301, the flame retardant layer 302, the compression resistant layer 303, the first heat conducting layer 304 and the second heat conducting layer 305 are all not more than two millimeters.
Because the graphene material and the copper metal material have good heat conduction performance, heat can be conducted outside the carbon fiber composite board, the situation that the carbon fiber composite board is prevented from icing is prevented, the utilization efficiency of airborne energy is greatly improved, the burden of the overall design of an aircraft is reduced, ice which is externally bonded by the carbon fiber composite board can be melted, and the safety performance of the aircraft is ensured.
Standard parts used in the method can be purchased from the market, special-shaped parts can be customized according to description of specifications and drawings, specific connection modes of the parts are conventional means such as mature bolts, rivets and welding in the prior art, machines, parts and equipment are conventional in the prior art, and circuit connection is conventional in the prior art, so that the special-shaped parts are not described in detail.
The working principle of the embodiment is as follows:
(1) The first adhesive layer 201 is made of a heat-conducting pouring sealant material, the heat-conducting pouring sealant is a double-component condensation heat-conducting pouring sealant, sensitive circuits and components can be reliably protected for a long time in wide temperature and humidity changes, the heat-conducting pouring sealant has excellent electrical insulation performance, can resist environmental pollution, avoids damage to products caused by environmental factors such as stress, vibration and humidity, is particularly suitable for products with good heat dissipation performance required by the pouring sealant, the products have excellent physical and chemical resistance performance, the ultraviolet-proof layer 202 is made of an acrylic material, the weather resistance, the heat resistance and the ultraviolet resistance of the acrylic material are good, the cracking deformation of a base surface can be adapted to a certain extent, the sound-proof layer 203 is made of a sound-proof damping adhesive material, the sound-proof damping adhesive plays a key role in weakening and attenuating sound transmission, the sound has good blocking effect, the tensile layer 204 is made of a polyester fiber material, and the maximum advantages of crease resistance and shape retention are good, the strength and the elastic recovery capability are strong and durable, and the tensile performance of the carbon fiber-proof composite board can be improved.
(2) The cold-resistant layer 205 is made of thermoplastic polyester elastomer material, because the thermoplastic polyester elastomer has good cold-resistant capability, and meanwhile, the impact resistance of the thermoplastic polyester elastomer under the low temperature condition is very excellent, the cold-resistant layer meets the high-altitude flight condition of an airplane, the carbon fiber-resistant composite board can be effectively prevented from being frozen out during flight, the flight safety of the airplane is ensured, the second adhesive layer 301 is made of heat-conducting silica gel material, the heat-conducting silica gel is high-end heat-conducting compound, and is not solidified, the risk of circuit short circuit and the like can be avoided due to the non-conductive characteristic, the heat-conducting bonding sealing silica gel is single-component, heat-conducting and room-temperature-curing organic silicon bonding sealing gel, the flame-retardant layer 302 is made of polyvinyl chloride material, because the polyvinyl chloride material has good flame retardant property, can improve this prevent carbon fiber composite sheet's flame retardant property, compressive layer 303 selects polypropylene material, and polypropylene material possesses good compressive property, can improve the compressive property of preventing carbon fiber composite sheet, has guaranteed the security performance of aircraft, and first heat conduction layer 304 and second heat conduction layer 305 select respectively to use graphene material and copper metal material, because graphene material and copper metal material's good heat conductivility can make heat conduction outside preventing carbon fiber composite sheet, prevent the frozen condition of preventing carbon fiber composite sheet and take place, improve the utilization efficiency of airborne energy by a wide margin, reduce the burden of aircraft overall design, can make the ice of preventing carbon fiber composite sheet outer knot can melt, guaranteed the security performance of aircraft.
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. The utility model provides a fire prevention aircraft deicing is with preventing carbon fiber composite sheet, includes basic unit (1), its characterized in that: the upper surface of the base layer (1) is provided with a cold-resistant component (2), and the lower surface of the base layer (1) is provided with a heat-conducting component (3);
the cold-resistant component (2) comprises a first adhesive layer (201) arranged on the upper surface of a base layer (1), an ultraviolet-proof layer (202) is fixed on the upper surface of the first adhesive layer (201), a sound blocking layer (203) is fixed on the upper surface of the ultraviolet-proof layer (202), a tensile layer (204) is fixed on the upper surface of the sound blocking layer (203), and a cold-resistant layer (205) is fixed on the upper surface of the tensile layer (204).
2. An anti-carbon fiber composite board for deicing a fire-resistant aircraft as recited in claim 1, wherein: the first adhesive layer (201) is a heat conduction pouring sealant layer, and the ultraviolet-proof layer (202) is an acrylic coating.
3. An anti-carbon fiber composite board for deicing a fire-resistant aircraft as recited in claim 1, wherein: the sound blocking layer (203) is a sound insulation damping glue layer, and the tensile layer (204) is a polyester fiber coating.
4. An anti-carbon fiber composite board for deicing a fire-resistant aircraft as recited in claim 1, wherein: the cold-resistant layer (205) is a thermoplastic polyester elastomer layer, and the thicknesses of the first adhesive layer (201), the ultraviolet-proof layer (202), the sound-blocking layer (203), the tensile layer (204) and the cold-resistant layer (205) are not more than two millimeters.
5. An anti-carbon fiber composite board for deicing a fire-resistant aircraft as recited in claim 1, wherein: the heat conduction assembly (3) comprises a second adhesive layer (301) arranged on the lower surface of the base layer (1), a flame retardant layer (302) is fixed on the lower surface of the second adhesive layer (301), a compression resistant layer (303) is fixed on the lower surface of the flame retardant layer (302), a first heat conduction layer (304) is fixed on the lower surface of the compression resistant layer (303), and a second heat conduction layer (305) is fixed on the lower surface of the first heat conduction layer (304).
6. An anti-carbon fiber composite board for deicing a fire-resistant aircraft as recited in claim 5, wherein: the second adhesive layer (301) is a heat-conducting silica gel layer, and the flame-retardant layer (302) is a polyvinyl chloride coating.
7. An anti-carbon fiber composite board for deicing a fire-resistant aircraft as recited in claim 5, wherein: the compression-resistant layer (303) is a polypropylene coating, and the first heat-conducting layer (304) is a graphene coating.
8. An anti-carbon fiber composite board for deicing a fire-resistant aircraft as recited in claim 5, wherein: the second heat conduction layer (305) is a copper metal layer, and the thicknesses of the second adhesive layer (301), the flame retardant layer (302), the compression resistant layer (303), the first heat conduction layer (304) and the second heat conduction layer (305) are not more than two millimeters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223449111.XU CN218966364U (en) | 2022-12-23 | 2022-12-23 | Fireproof carbon fiber composite board for deicing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223449111.XU CN218966364U (en) | 2022-12-23 | 2022-12-23 | Fireproof carbon fiber composite board for deicing aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN218966364U true CN218966364U (en) | 2023-05-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223449111.XU Active CN218966364U (en) | 2022-12-23 | 2022-12-23 | Fireproof carbon fiber composite board for deicing aircraft |
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| Country | Link |
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| CN (1) | CN218966364U (en) |
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- 2022-12-23 CN CN202223449111.XU patent/CN218966364U/en active Active
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