CN213566509U - Graphite alkene film electric heat defroster - Google Patents
Graphite alkene film electric heat defroster Download PDFInfo
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- CN213566509U CN213566509U CN202022222059.9U CN202022222059U CN213566509U CN 213566509 U CN213566509 U CN 213566509U CN 202022222059 U CN202022222059 U CN 202022222059U CN 213566509 U CN213566509 U CN 213566509U
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Abstract
The utility model discloses a graphite alkene film electric heat defroster belongs to aircraft deicing technical field. This graphite alkene film electric heat defroster includes: the deicing device comprises a graphene electrothermal film, a porous film and a skin, capillary vent pipes are attached to the left side and the right side of the porous film, capillary vent holes are formed in two side walls of a pipeline of the capillary vent pipes in the horizontal direction, the capillary vent holes are tightly attached to the side walls of the porous film, and dense air injection through holes are formed in the surface of the skin; the air supply device comprises an air supply pump and a vent pipe, wherein an air inlet of the air supply pump is communicated with the atmosphere, an air outlet of the air supply pump is connected with the vent pipe, and the vent pipe is communicated with the capillary vent pipe. The utility model discloses a defroster can utilize the heat-conduction mode of heating graphite alkene electric heat membrane to heat the deicing to the ice sheet, still utilizes the heat convection mode of heated air to come for aircraft surface deicing, and the heated air can also form the air supporting effect between ice sheet and the device moreover, accelerates deicing efficiency greatly.
Description
Technical Field
The utility model relates to an aircraft deicing technical field, concretely relates to graphite alkene film electric heat defroster.
Background
With the rapid development of economy in China, the air transportation industry is developed vigorously, but the icing of the airplane threatens the flight safety all the time, and the icing is a common phenomenon, but when the front edges of wings and empennages are iced, the wing profiles are changed, the lift force is reduced, the resistance is increased, and the stability of the airplane is damaged. The ice prevention and the ice removal of the airplane are important problems for ensuring the safety of the airplane. Four phases in which aircraft icing can occur: ground, take-off, level flight, landing, etc. When the airplane stays on the ground, the air temperature is close to or lower than 0 degree, or when rainfall, snow and frost exist, the surface of the airplane can be frozen. When the airplane flies in a convection cloud layer with the altitude of below 7000 m, because supercooled water drops are distributed in the cloud layer, the supercooled water drops can impact the windward surface of the airplane and can be rapidly frozen into ice due to the difference between the internal temperature and the external temperature.
The current mainstream airplane anti-icing and deicing mode is electrothermal deicing: the heating element in the shape of a strip, a wire or a film is embedded into the structure of the part of the airplane easy to freeze, and the heating element is electrified and heated to prevent and remove ice, so that the method is simple and easy to operate, and has a good effect. However, if the single heat conduction mode is adopted for deicing, the problems of low efficiency, long deicing time, slow reaction speed and the like exist. In order to solve the problems, a graphene film electric heating deicing device capable of deicing through a heat conduction mode and deicing through heat convection and an air floatation effect is provided.
SUMMERY OF THE UTILITY MODEL
The utility model aims at overcoming the short slab among the prior art, provide a graphite alkene film electric heat defroster.
The utility model provides a graphite alkene film electric heat defroster, include:
the deicing composite membrane comprises a graphene electrothermal membrane, a porous membrane and a skin, wherein the graphene electrothermal membrane is arranged on the surface of an airplane wing, the graphene electrothermal membrane is electrically connected with a power module, the porous membrane is attached to the graphene electrothermal membrane, the porous membrane is made of porous breathable and high-temperature-resistant materials, capillary vent pipes are respectively attached to the edges of the porous membrane, capillary vent holes are formed in the side walls of capillary vent pipe pipelines, the capillary vent holes are tightly attached to the side walls of the edges of the porous membrane, the skin is attached to the porous membrane and the capillary vent pipes, and dense air injection through holes are formed in the surface of the skin;
and the air supply device is communicated with the capillary air inlet of the capillary air pipe and is used for supplying air to the capillary air pipe of the whole deicing composite membrane.
Preferably, the air feeder includes air feed pump, main breather pipe and vice breather pipe, the air inlet and the atmosphere intercommunication of air feed pump, the gas outlet with the air inlet intercommunication of main breather pipe, air feed pump and power module electricity are connected, and main breather pipe pipeline lateral wall is equipped with main vent hole, main vent hole and vice breather pipe air inlet intercommunication, vice breather pipe wall are provided with vice vent hole, vice vent hole communicates with the capillary air inlet of capillary breather pipe.
Preferably, a piezoelectric material layer is arranged between the porous membrane and the skin, the piezoelectric material layer can generate deformation or vibration after being electrified, dense air injection through holes are formed in the surface of the piezoelectric material layer, and the piezoelectric material layer is electrically connected with the power module.
Preferably, a heat-conducting silica gel layer is arranged between the piezoelectric material layer and the porous membrane, dense air injection through holes are formed in the surface of the heat-conducting silica gel layer, and a heat-insulating material layer is arranged between the graphene electrothermal film and the surface of the airplane wing.
Preferably, the temperature sensor is arranged between the porous membrane and the graphene electrothermal film, the temperature sensor is electrically connected with the controller, and the graphene electrothermal film is electrically connected with the controller.
Preferably, the capillary snorkel pipe is located on the graphene electrothermal film.
Preferably, the air supply pump air inlet is provided with an air filter.
Preferably, the porous membrane is copper foam.
Preferably, the skin is hydrophobic.
Compared with the prior art, the beneficial effects of the utility model are that: the utility model discloses a defroster can utilize the heat-conduction mode of heating graphite alkene electric heat membrane to heat the deicing to the ice sheet, can also utilize the heat convection mode of heated air to come for aircraft surface deicing, and the heated air can also form the air supporting effect between ice sheet and the device moreover, accelerates deicing efficiency greatly. The piezoelectric material layer can generate mechanical deformation or vibration after being electrified, so that the deicing efficiency can be further accelerated. The heat-conducting silica gel can play a role in insulation and reduction of thermal contact resistance, and further protects components and accelerates heat transfer. The hydrophobic skin can accelerate the sliding of the crushed ice blocks and prevent water vapor from attaching to the surface of the skin for secondary icing.
Drawings
Fig. 1 is a schematic structural view of a deicing composite film according to example 1 of the present invention;
FIG. 2 is a schematic structural view of the air supply device of the present invention;
fig. 3 is a schematic structural view of a deicing composite film according to embodiment 2 of the present invention;
fig. 4 is a schematic structural view of a deicing composite film according to embodiment 3 of the present invention;
fig. 5 is a schematic three-dimensional view of a deicing composite film according to example 3 of the present invention;
fig. 6 is a schematic view of the capillary vent of the present invention.
Description of reference numerals:
1. the deicing composite membrane comprises 101 parts of a thermal insulation material layer, 102 parts of a graphene electrothermal film, 103 parts of a porous membrane, 104 parts of a skin, 105 parts of a piezoelectric material layer, 106 parts of a heat conduction silica gel layer, 107 parts of a temperature sensor, 108 parts of an air injection through hole, 2 parts of an air supply device, 201 parts of a capillary vent pipe, 202 parts of a capillary vent hole, 203 parts of an air supply pump, 204 parts of a main vent pipe, 205 parts of the main vent hole, 206 parts of the capillary air inlet, 207 parts of an auxiliary vent pipe, 208 parts of the auxiliary vent hole, 209 parts of an.
Detailed Description
The following detailed description of the present invention is provided in conjunction with the accompanying fig. 1-6, but it should be understood that the scope of the present invention is not limited by the following detailed description. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
Example 1
As shown in the figure, the utility model provides a pair of graphite alkene film electric heat defroster, include:
the deicing composite film 1 comprises a graphene electrothermal film 102, a porous film 103 and a skin 104, wherein the graphene electrothermal film 102 is arranged on the surface of an airplane wing, the graphene electrothermal film 102 is electrically connected with a power module, the porous film 103 is attached to the graphene electrothermal film 102, the porous film 103 is made of porous breathable and high-temperature-resistant materials, capillary vent pipes 201 are respectively attached to the edges of the porous film 103, capillary vent holes 202 are formed in the side walls of the capillary vent pipes 201, the capillary vent holes 202 are tightly attached to the side walls of the edges of the porous film 103, the skin 104 is attached to the porous film 103 and the capillary vent pipes 201, and dense air injection through holes 108 are formed in the surface of the skin 104;
and the air supply device 2 is communicated with the capillary air inlet 206 of the capillary air vent pipe 201 and is used for supplying air to the capillary air vent pipe 201 of the whole deicing composite film 1.
Wherein, gas supply device 2 includes air feed pump 203, main breather pipe 204 and vice breather pipe 207, the air inlet and the atmosphere intercommunication of air feed pump 203, the gas outlet with the air inlet intercommunication of main breather pipe 204, air feed pump 203 are connected with the power module electricity, and main breather pipe 204 pipeline lateral wall is equipped with main vent 205, main vent 205 and vice breather pipe 207 air inlet intercommunication, vice breather pipe 207 wall is provided with vice vent 208, vice vent 208 communicates with the capillary air inlet 206 of capillary breather pipe 201.
The working principle of example 1 is now briefly described:
the deicing composite membrane comprises a plurality of deicing composite membranes, wherein the deicing composite membranes are spliced and covered on the surface of an airplane wing, air is pumped into a main vent pipe through an air supply pump, enters a plurality of auxiliary vent pipes through a main vent hole in the side wall of the main vent pipe, enters a plurality of capillary vent pipes through auxiliary vent holes in the side wall of the auxiliary vent pipe, finally enters a porous thin film layer in the deicing composite membrane through capillary vent holes in the side wall of the capillary vent pipe, and is heated by a graphene electrothermal film at the bottom layer of the. The heated hot air is sprayed out through the air injection through holes of the skin layer, the deicing composite film and the gap between the ice layers covering the surface of the deicing composite film are sprayed, the ice layers are heated by utilizing a thermal convection mode, and the hot air forms an air floatation effect between the deicing composite film and the ice layers, so that the ice layers are supported, and the deicing efficiency is accelerated. In addition, the heat that graphite alkene electric heat membrane produced can conduct to the ice sheet through porous thin film layer and skin layer, carries out the direct heating to the ice sheet, and then reaches the purpose of deicing.
Example 2
To further accelerate the deicing efficiency, the present example 1 was followed.
The piezoelectric material layer 105 is arranged between the porous membrane and the skin, the piezoelectric material layer 105 can generate deformation or vibration after being electrified, dense air injection through holes 108 are formed in the surface of the piezoelectric material layer 105, and the piezoelectric material layer 105 is electrically connected with the power supply module.
The working principle of example 2 will now be briefly described:
the piezoelectric material layer can generate mechanical deformation or vibration after being electrified, so that a larger gap is generated between the ice layer and the deicing composite film, a large-area whole ice block can be vibrated and broken into small ice blocks, and the deicing efficiency is further accelerated.
Example 3
On the basis of embodiment 2, in order to prevent the electric leakage of components and prevent the heat loss caused by the heat conduction of the airplane wing.
A heat-conducting silica gel layer 106 is arranged between the piezoelectric material layer 105 and the porous membrane 103, dense air injection through holes 108 are formed in the surface of the heat-conducting silica gel layer 106, and a heat-insulating material layer 101 is arranged between the graphene electrothermal film 102 and the surface of the airplane wing.
The working principle of example 3 will now be briefly described:
the heat-conducting silica gel layer can play the role of insulation and reduction of thermal contact resistance, so that components and parts are protected to accelerate heat transfer, and the heat-insulating material layer prevents heat from being led out and lost from the wings of the airplane.
Example 4
On the basis of embodiment 2 or 3, in order to prevent that the graphite alkene electric heat membrane from overheating and causing the damage to components and parts.
The temperature sensor 107 is arranged between the porous membrane 103 and the graphene electrothermal film 102, the temperature sensor 107 is electrically connected with a controller, and the graphene electrothermal film 102 is electrically connected with the controller.
The working principle of example 3 will now be briefly described: temperature sensor monitoring real-time temperature information, signal transmission to controller, the operating condition of graphite alkene electric heat membrane is adjusted in real time according to temperature information to the controller.
Preferably, the capillary snorkel 201 is located on the graphene electrothermal film 102. When the capillary vent pipe conducts air, the lower graphene electrothermal film heats air incidentally
Preferably, an air filter 209 is provided at the air inlet of the air supply pump 203. Preventing impurities in the air from blocking the air injection through holes.
In a preferred embodiment, the porous membrane 103 is a copper foam. The foam copper is porous and breathable, high-temperature resistant and fast in heat conduction.
Preferably, the skin 104 is hydrophobic. The hydrophobic skin can accelerate the sliding of the crushed ice blocks and prevent water vapor from attaching to the surface of the skin for secondary icing.
Although embodiments of the present invention 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 in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (9)
1. A graphite alkene film electric heat defroster which characterized in that includes:
the deicing composite film (1) comprises a graphene electrothermal film (102), a porous film (103) and a skin (104), wherein the graphene electrothermal film (102) is arranged on the surface of an airplane wing, the graphene electrothermal film (102) is electrically connected with a power supply module, the porous film (103) is attached to the graphene electrothermal film (102), the porous film (103) is made of a porous breathable and high-temperature-resistant material, capillary vent pipes (201) are respectively attached to the edges of the porous film (103), capillary vent holes (202) are formed in the side wall of the pipeline of each capillary vent pipe (201), the capillary vent holes (202) are tightly attached to the side wall of the edge of the porous film (103), the skin (104) is attached to the porous film (103) and the capillary vent pipes (201), and dense air injection through holes (108) are formed in the surface of the skin;
and the gas supply device (2) is communicated with the capillary gas inlet (206) of the capillary gas vent pipe (201) and is used for supplying gas to the capillary gas vent pipe (201) of the whole deicing composite film (1).
2. The graphene film electrothermal deicing device according to claim 1, wherein the gas supply device (2) comprises a gas supply pump (203), a main vent pipe (204) and a sub vent pipe (207), wherein a gas inlet of the gas supply pump (203) is communicated with the atmosphere, a gas outlet of the gas supply pump is communicated with a gas inlet of the main vent pipe (204), the gas supply pump (203) is electrically connected with the power module, a main vent hole (205) is formed in a pipeline side wall of the main vent pipe (204), the main vent hole (205) is communicated with a gas inlet of the sub vent pipe (207), a sub vent hole (208) is formed in a wall of the sub vent pipe (207), and the sub vent hole (208) is communicated with a capillary gas inlet (206) of the capillary vent pipe (201.
3. The graphene film electrothermal deicing device according to claim 1, wherein a piezoelectric material layer (105) is arranged between the porous film (103) and the skin (104), the piezoelectric material layer (105) can generate deformation or vibration after being electrified, dense air injection through holes (108) are formed in the surface of the piezoelectric material layer (105), and the piezoelectric material layer (105) is electrically connected with a power module.
4. The graphene film electrothermal deicing device according to claim 3, wherein a heat-conducting silica gel layer (106) is arranged between the piezoelectric material layer (105) and the porous film (103), dense air injection through holes (108) are arranged on the surface of the heat-conducting silica gel layer (106), and a heat-insulating material layer (101) is arranged between the graphene electrothermal film (102) and the surface of the airplane wing.
5. The graphene film electrothermal deicing device according to claim 1, wherein a temperature sensor (107) is arranged between the porous film (103) and the graphene electrothermal film (102), the temperature sensor (107) is electrically connected with a controller, and the graphene electrothermal film (102) is electrically connected with the controller.
6. The graphene film electrothermal deicing device according to claim 1, wherein the capillary snorkel (201) pipe is located above the graphene electrothermal film (102).
7. Graphene film electrothermal deicing device according to claim 2, wherein an air filter (209) is provided at an air inlet of the air supply pump (203).
8. The graphene film electrothermal deicing device according to claim 1, wherein the porous film (103) is copper foam.
9. Graphene film electrothermal deicing device according to claim 1, wherein the skin (104) is hydrophobic.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022222059.9U CN213566509U (en) | 2020-09-30 | 2020-09-30 | Graphite alkene film electric heat defroster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022222059.9U CN213566509U (en) | 2020-09-30 | 2020-09-30 | Graphite alkene film electric heat defroster |
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| Publication Number | Publication Date |
|---|---|
| CN213566509U true CN213566509U (en) | 2021-06-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022222059.9U Active CN213566509U (en) | 2020-09-30 | 2020-09-30 | Graphite alkene film electric heat defroster |
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| CN (1) | CN213566509U (en) |
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