CN112757717A - Directional heat conduction electric heating device and preparation method - Google Patents

Directional heat conduction electric heating device and preparation method Download PDF

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Publication number
CN112757717A
CN112757717A CN202110038866.1A CN202110038866A CN112757717A CN 112757717 A CN112757717 A CN 112757717A CN 202110038866 A CN202110038866 A CN 202110038866A CN 112757717 A CN112757717 A CN 112757717A
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China
Prior art keywords
layer
heat conduction
insulating layer
heating
electric heating
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CN202110038866.1A
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Chinese (zh)
Inventor
王岩
段沐枫
高丽敏
徐吉峰
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Commercial Aircraft Corp of China Ltd
Beijing Aeronautic Science and Technology Research Institute of COMAC
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Commercial Aircraft Corp of China Ltd
Beijing Aeronautic Science and Technology Research Institute of COMAC
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Priority to CN202110038866.1A priority Critical patent/CN112757717A/en
Publication of CN112757717A publication Critical patent/CN112757717A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B3/00—Ohmic-resistance heating
    • H05B3/02—Details
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B3/00—Ohmic-resistance heating
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    • H05B3/12—Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material
    • H05B3/14—Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
    • H05B3/145—Carbon only, e.g. carbon black, graphite
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B3/00—Ohmic-resistance heating
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  • Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Surface Heating Bodies (AREA)
  • Resistance Heating (AREA)

Abstract

The invention relates to a directional electric heating heat conduction device and a preparation method thereof, which are used for deicing wings or slats of an airplane, wherein the device sequentially comprises a protective layer, a heat conduction layer, a first insulating layer, a heating layer, a second insulating layer, a heat insulation layer, a third insulating layer and a substrate layer from outside to inside; the directional electric heating heat conduction device also comprises a lead wire used for connecting an external power supply; the wire is in contact with the heating layer, is led out from the heating layer, penetrates through the second insulating layer and the heat insulating layer, extends out of the device and is reserved with a certain length. The device can realize heating deicing with low energy consumption, has high-temperature protection effect on the matrix, and can finally improve the energy efficiency of the airplane.

Description

Directional heat conduction electric heating device and preparation method
Technical Field
The invention relates to a directional heat conduction electric heating device and a preparation method thereof, belonging to the field of aerospace deicing prevention.
Background
In the prior art, the leading edge of the wing and the surface of the slat of an airplane can be frozen due to the fact that supercooled liquid drops are collided at low temperature in the normal flight process. After the aircraft freezes, not only flight weight increases, and aerodynamic configuration can suffer destruction moreover, makes the lift of aircraft reduce, and maneuverability and stability descend to bring irreparable consequence for the flight of aircraft. Aiming at the problem of icing, advanced models such as B787 and the like adopt a metal electric heating mode to prevent and remove ice on the positions such as the wing leading edge of an airplane. B787 adopts a GKN metal thermal spraying technology to use a metal coating as a heating element, but the technology is too high in manufacturing cost, the spraying process has certain pollution to the environment, the metal coating has large self weight, and in addition, for the base structures of wings, slats and the like of an airplane made of composite materials, the high temperature during electric heating is very easy to cause the aging and structural damage of the base materials.
In view of the above disadvantages of the metal electrical heating technology, the chinese invention patent (CN110510102A) discloses a attachable self-resistance heating/super-hydrophobic integrated gradient film material, which is made of adhesive resin, insulating resin, heat and electricity conductive filler and heat and electricity insulating filler. However, in the film material, it is very difficult to uniformly distribute the filler added in the matrix, which may cause uneven temperature distribution, even local over-high temperature, and the distribution and arrangement of the circuit electrodes are also highly required. In addition, the heat insulating resin used in the heat insulating material of the present invention is a low surface energy material, which is difficult to mold and has a general heat insulating effect.
The Chinese invention patent (CN110481795A) discloses an anti-icing and deicing device of a helicopter rotor made of graphene composite materials and a manufacturing method thereof, and the anti-icing and deicing device is designed for the helicopter rotor and comprises a skin, an insulating heat transfer layer, a heating layer and an insulating heat insulation layer. But this prevent and remove ice device passes through the structural adhesive bonding together as outer fringe body and basal body structure, and the resistance wire is selected to the zone of heating, and this kind of heating mode easily causes heating temperature's uneven distribution, and the resistance wire buckling point easily damages, and insulating thermal-insulated layer adopts carbon fiber and epoxy material simultaneously, takes place thermal ageing destruction easily and thermal-insulated effect general.
Therefore, it is necessary to develop a directional heat-conducting electric heating structure with uniform heating effect, high heat transfer/insulation efficiency, and easy realization of electrode connection and arrangement.
Disclosure of Invention
The invention aims to provide a directional heat conduction electric heating device and a preparation method thereof, wherein the directional heat conduction electric heating device is a multilayer functional device, has the function of directionally conducting electric heating heat to the outside of a wing, has low cost and high energy efficiency compared with the electric heating device in the prior art, and has a protection effect on parts or devices which cannot bear high temperature in the wing.
The invention provides a directional electric heating heat conduction device, which is used for deicing wings or slats of an airplane and is of a layered structure, and the directional electric heating heat conduction device sequentially comprises a protective layer, a heat conduction layer, a first insulating layer, a heating layer, a second insulating layer, a heat insulation layer, a third insulating layer and a substrate layer from outside to inside;
the directional electric heating heat conduction device also comprises a lead wire used for connecting an external power supply;
the wire contacts the heating layer, is led out from the heating layer, penetrates through the second insulating layer and the heat insulating layer, extends out of the device and is reserved with a certain length.
Furthermore, the heating layer is made of carbon nanotube films and used for converting electric energy into heat energy.
Further, the first insulating layer, the second insulating layer and the third insulating layer are all glass fiber layers.
Further, the heat insulation layer is made of silicon dioxide nanometer microporous aerogel, and the thickness of the heat insulation layer is 1mm-6 mm.
Further, the protective layer comprises an adhesive and a heat conduction functional layer, the heat conduction functional layer is a metal thin layer, and the thickness of the metal thin layer is not more than 2 mm.
Furthermore, the heat conducting layer is made of a carbon nanotube array or graphene-doped resin matrix material, and the heat conducting layer conducts heat unidirectionally.
Further, the first insulating layer and the second insulating layer cover the whole heating layer, and the part of the lead contacting the heating layer is coated with high-temperature-resistant conductive adhesive.
Further, the first insulating layer, the second insulating layer and the third insulating layer are all glass fiber layers.
Further, the heat insulation layer is made of silicon dioxide nanometer microporous aerogel, and the thickness of the heat insulation layer is 1mm-6 mm.
Further, the protective layer comprises an adhesive and a heat conduction functional layer, the heat conduction functional layer is a metal thin layer, and the thickness of the metal thin layer is not more than 2 mm.
Furthermore, the heat conducting layer is made of a carbon nanotube array or graphene-doped resin matrix material, and the heat conducting layer conducts heat unidirectionally.
Further, the first insulating layer and the second insulating layer cover the whole heating layer, and the part, which is extended out of the device and is reserved with a certain length, of the wire, which is in contact with the heating layer, is coated with high-temperature-resistant conductive adhesive.
Further, the invention also provides a preparation method of the directional electric heating heat conduction device, which comprises the following steps:
(1) performing semi-curing treatment on the second insulating layer, the third insulating layer, the heat insulating layer and the conducting wire to prepare a pre-forming body;
(2) prefabricating the heating layer on the first insulating layer in a pre-forming mode;
(3) sequentially splicing the substrate layer, the preformed body, the heating layer, the first insulating layer and the heat conduction layer from inside to outside and then carrying out complete curing treatment to obtain a cured body;
(4) and bonding the solidified body and the protective layer together by using an adhesive.
Further, the complete curing treatment adopts a mode of compression molding or entering an autoclave.
Furthermore, the high temperature resistant temperature of the adhesive is more than 180 ℃.
The invention has the advantages of
The directional electric heating heat conduction device has the following beneficial effects:
(1) according to the directional electric heating heat conduction device provided by the invention, the heat insulation layer uses the nano micropore aerogel, the heat insulation effect is higher than that of static air, the heat insulation effect is shock insulation and water insulation effects, the heat insulation device has a protection effect on wires in the heat insulation layer, the density is low, and the weight is small.
(2) The heating layer is made of carbon nanotube film materials, so that the heating is uniform, wiring and electrode connection are convenient, and the cost is low compared with the traditional metal heating film materials.
(3) The heat conducting layer is one-way heat conducting, has directionality and can realize directional heat conduction, and is favorable for conducting heat to the surface of a wing or a slat of an airplane.
(4) The invention can realize heating deicing with low energy consumption, has high-temperature protection effect on the matrix, and can finally improve the energy efficiency of the airplane.
(5) The surface of the protective layer adopts the metal thin layer, so that damage to the directional heat conduction electric heating device caused by impact of external substances can be prevented, and the metal heat transfer coefficient is high, so that heat can be favorably diffused to the surface of the wing or slat of the airplane.
Drawings
Fig. 1 is a schematic view of a directional electrical heating heat conduction structure according to the present invention.
In the figure: 1. the heat-conducting type LED lamp comprises a protective layer, 2 heat-conducting layers, 3 first insulating layers, 3 'second insulating layers, 3'. third insulating layers, 4 heating layers, 5 heat-insulating layers, 6 substrate layers and 7 conducting wires.
Detailed Description
In order to better understand the technical solution of the present invention, the present disclosure includes but is not limited to the following detailed description, and similar techniques and methods should be considered as within the scope of the present invention. In order to make the technical problems, technical solutions and advantages of the present invention more apparent, the following detailed description is given with reference to the accompanying drawings and specific embodiments.
It should be understood that the described embodiments of the invention are only some embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in the examples of the present invention and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.
As shown in fig. 1, an embodiment of the present invention provides a directional electrical heating heat conduction device for deicing a wing or a slat of an aircraft. The device is directly covered on the surface of the wing or slat of the airplane and is used for timely removing icing generated on the surface of the wing or slat of the airplane in the flying process of the airplane. The directional electrical heating heat conduction device sequentially comprises a protective layer 1, a heat conduction layer 2, a first insulation layer 3, a heating layer 4, a second insulation layer 3 ', a heat insulation layer 5, a third insulation layer 3', a base layer 6 and a wire 7 from outside to inside, wherein the protective layer 1 comprises an adhesive and a heat conduction functional layer, and the adhesive is bonded with the heat conduction functional layer.
Preferably, the wire 7 is in contact with the heating layer 2, and a certain length is reserved outside the directional electric heating heat conduction device after being led out from the heating layer 2 and passing through the second insulation layer 3' and the insulation layer 5.
Preferably, the first insulating layer 3, the second insulating layer 3' and the third insulating layer 3 ″ are all made of glass fiber.
Preferably, the insulating layer 5 in this embodiment is silica nanoporous aerogel.
Preferably, the heating layer 4 is made of a carbon nanotube film material, and is used for converting electric energy into heat energy, and the size of the heat energy can be designed according to the voltage of an external power supply and a set control rate, and the thickness and the pattern of the heating layer 4 can be cut.
Preferably, the heat conduction layer 2 is made of a carbon nanotube array material or a graphene-doped resin matrix material, and the heat conduction layer 2 conducts heat in a unidirectional manner and has the function of directional heat transfer.
Preferably, the heat-conducting functional layer of the protective layer 1 is made of a metal thin layer material, and is of a curved surface structure, and the contour of the curved surface is consistent with the surface of the wing or the slat, so that the directional heat-conducting electric heating device can be completely attached to the surface of the wing or the slat of the airplane, meanwhile, the thickness of the metal thin layer is not more than 2mm to avoid the large self weight of the metal thin layer, the protective layer 1 is made of the metal thin layer, the damage to the directional heat-conducting electric heating device caused by low-energy impact of external substances can be prevented by the metal thin layer, the heat transfer coefficient of metal is high, and the heat generated by the directional heat-conducting electric heating device.
Preferably, the adhesive for the protective layer 1 is an epoxy resin adhesive or a high-temperature cured structural adhesive.
Preferably, the protective layer 1 and the heat conductive layer 2 are bonded together by an adhesive resistant to high temperatures of 180 ℃ or more, so as to efficiently transfer the internal heating temperature to the protective layer 1 made of a thin metal layer, in the present device, the protective layer 1 is disposed on the outermost side, and the heat conductive layer 2 is disposed between the protective layer 1 and the first insulating layer 3.
Preferably, the first and second insulating layers 3, 3' cover the entire heating layer 4, in order to prevent the current of the heating layer 4 introduced by the wires 7 during heating from leaking to the wing surface of the aircraft, generating damage to the wing or slat surface of the aircraft and wasting energy.
Preferably, the substrate layer 6 in this embodiment is made of a carbon fiber or glass fiber composite material.
Preferably, one end of the reserved lead 7 contacting the electric heating layer 2 is coated with a high temperature resistant conductive adhesive.
As a preferred scheme, the first, second and third insulating layers 3, 3 'and 3' all adopt glass fiber layers, wherein the glass fiber layers adopted by the two insulating layers formed by the second insulating layer 3 'and the third insulating layer 3' and the heat-insulating layer 5 adopting silica nano microporous aerogel are preformed, a lead 7 with enough length is reserved on the outer side edge of the preformed body formed by processing, the thickness of the heat-insulating layer 5 is set between 1mm and 6mm, the lead 7 is selected according to the requirement of temperature gradient, a reserved end is arranged on the outer side of the device and is coated with high-temperature-resistant conductive adhesive, and the lead 7 penetrating through the heat-insulating layer 5 is protected by the heat-insulating layer 5, so that the lead 7 is damped and water vapor isolated, the service life of the directional electric heating heat-conducting device is prolonged, and the occurrence of faults is reduced.
The preparation method of the directional electric heating heat conduction device comprises the following steps:
(1) performing semi-curing treatment on the second insulating layer, the third insulating layer, the heat insulating layer and the conducting wire to prepare a pre-forming body;
(2) prefabricating the heating layer on the first insulating layer in a pre-forming mode;
(3) sequentially splicing the substrate layer 6, the preformed body, the heating layer 4, the first insulating layer 3 and the heat conduction layer 2 from inside to outside, and then carrying out complete curing treatment to obtain a cured body;
(4) the cured body and the protective layer 1 are bonded together using an adhesive.
Wherein, the complete curing treatment can be carried out by compression molding or autoclave.
When the directional electric heating heat conduction device is used, the heating layer 4 is connected with an external power supply through a wire 7, the carbon nano tube film material can generate heat energy after the power supply is electrified, the generated heat energy is different according to different voltages adopted by the external power supply, most of the generated heat energy is directionally and unidirectionally conducted to an icing area on the surface of the wing or the slat of the airplane through the heat conduction layer 2, so that the heat energy is conducted to the surface of the wing or the slat of the airplane to melt an ice layer or an ice block generated on the surface of the wing or the slat of the airplane in the flying process, the directional heat conduction electric heating device is further provided with a heat insulation layer 5, the heat insulation layer 5 uses silicon dioxide nano micropore aerogel, the heat insulation effect is higher than that of static air, and the heat insulation layer 5 has the heat insulation effect on devices in the body of the airplane while the ice layer on the surface of the wing or the slat of the, the heat generated by the heating layer 4 is prevented from damaging components inside the airplane body, so that the normal flight of the airplane is ensured.
The foregoing description shows and describes several preferred embodiments of the invention, but as aforementioned, it is to be understood that the invention is not limited to the forms disclosed herein, but is not to be construed as excluding other embodiments and is capable of use in various other combinations, modifications, and environments and is capable of changes within the scope of the inventive concept as expressed herein, commensurate with the above teachings, or the skill or knowledge of the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the invention as defined by the appended claims.

Claims (10)

1. A directional electric heating heat conduction device is used for deicing wings or slats of an airplane and is characterized in that the directional electric heating heat conduction device is of a layered structure and sequentially comprises a protective layer, a heat conduction layer, a first insulation layer, a heating layer, a second insulation layer, a heat insulation layer, a third insulation layer and a substrate layer from outside to inside;
the directional electric heating heat conduction device also comprises a lead wire used for connecting an external power supply;
the wire contacts the heating layer, is led out from the heating layer, penetrates through the second insulating layer and the heat insulating layer, extends out of the device and is reserved with a certain length.
2. The device as claimed in claim 1, wherein the heating layer is made of carbon nanotube film for converting electric energy into heat energy.
3. The directional electric heating heat conduction device according to claim 1, wherein: the first insulating layer, the second insulating layer and the third insulating layer are all glass fiber layers.
4. The directional electric heating heat conduction device according to claim 1 or 2, wherein the thermal insulation layer is made of silica nano microporous aerogel, and the thickness of the thermal insulation layer is 1mm-6 mm.
5. The directional electric heating heat conduction device according to claim 4, wherein the protective layer comprises an adhesive and a heat conduction functional layer, the heat conduction functional layer is a metal thin layer, and the thickness of the metal thin layer is not more than 2 mm.
6. The directional electric heating heat conduction device according to claim 2, wherein the heat conduction layer is made of a carbon nanotube array or graphene-doped resin matrix material, and the heat conduction layer conducts heat unidirectionally.
7. The directional electric heating heat conduction device according to claim 1, wherein the first insulating layer and the second insulating layer cover the entire heating layer, and a portion of the wire in contact with the heating layer is coated with a high temperature resistant conductive adhesive.
8. A method for preparing a directional electric heating heat conduction device as claimed in any one of claims 1 to 7, characterized in that the method comprises the following steps:
(1) performing semi-curing treatment on the second insulating layer, the third insulating layer, the heat insulating layer and the conducting wire to prepare a pre-forming body;
(2) prefabricating the heating layer on the first insulating layer in a pre-forming mode;
(3) sequentially splicing the substrate layer, the preformed body, the heating layer, the first insulating layer and the heat conduction layer from inside to outside and then carrying out complete curing treatment to obtain a cured body;
(4) and bonding the solidified body and the protective layer together by using an adhesive.
9. Use according to claim 8, wherein the full-curing process is compression molding or autoclave.
10. The use method according to claim 9, wherein the adhesive has a high temperature resistance of 180 ℃ or higher.
CN202110038866.1A 2021-01-12 2021-01-12 Directional heat conduction electric heating device and preparation method Pending CN112757717A (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113502144A (en) * 2021-08-17 2021-10-15 北京理工大学 Directional heat conduction and insulation material and preparation method thereof
CN114150547A (en) * 2021-06-10 2022-03-08 西南交通大学 Directional heat transfer pavement applied to ice and snow melting in airport and control method thereof
WO2024078234A1 (en) * 2022-10-13 2024-04-18 中山大学 Heater, preparation method therefor, and application thereof

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114150547A (en) * 2021-06-10 2022-03-08 西南交通大学 Directional heat transfer pavement applied to ice and snow melting in airport and control method thereof
CN113502144A (en) * 2021-08-17 2021-10-15 北京理工大学 Directional heat conduction and insulation material and preparation method thereof
CN113502144B (en) * 2021-08-17 2022-04-29 北京理工大学 Directional heat conduction and insulation material and preparation method thereof
WO2024078234A1 (en) * 2022-10-13 2024-04-18 中山大学 Heater, preparation method therefor, and application thereof

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