CN114435597A - Temperature difference power generation device for wing anti-icing and deicing assembly, anti-icing and deicing assembly and method - Google Patents
Temperature difference power generation device for wing anti-icing and deicing assembly, anti-icing and deicing assembly and method Download PDFInfo
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- CN114435597A CN114435597A CN202210085662.8A CN202210085662A CN114435597A CN 114435597 A CN114435597 A CN 114435597A CN 202210085662 A CN202210085662 A CN 202210085662A CN 114435597 A CN114435597 A CN 114435597A
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- 238000000034 method Methods 0.000 title claims abstract description 20
- 238000010248 power generation Methods 0.000 title claims abstract description 16
- 238000010438 heat treatment Methods 0.000 claims abstract description 82
- 239000004065 semiconductor Substances 0.000 claims abstract description 49
- 230000000087 stabilizing effect Effects 0.000 claims abstract description 13
- 238000009413 insulation Methods 0.000 claims abstract description 12
- 230000005611 electricity Effects 0.000 claims description 3
- 230000004913 activation Effects 0.000 claims 1
- 239000011248 coating agent Substances 0.000 abstract description 2
- 238000000576 coating method Methods 0.000 abstract description 2
- 238000004134 energy conservation Methods 0.000 abstract description 2
- 230000007613 environmental effect Effects 0.000 abstract description 2
- 230000005676 thermoelectric effect Effects 0.000 abstract description 2
- 238000005485 electric heating Methods 0.000 description 6
- 239000003365 glass fiber Substances 0.000 description 3
- 230000002265 prevention Effects 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000013329 compounding Methods 0.000 description 2
- 239000003822 epoxy resin Substances 0.000 description 2
- 229910021389 graphene Inorganic materials 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 229920000647 polyepoxide Polymers 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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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
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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
- B64D15/20—Means for detecting icing or initiating de-icing
- B64D15/22—Automatic initiation by icing detector
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Abstract
The invention provides a temperature difference power generation device for an anti-icing and deicing component of a wing, the anti-icing and deicing component and a method, wherein the anti-icing and deicing component comprises a heat insulation layer, a heating layer and a heat transfer layer which are sequentially attached, a temperature difference heating module semiconductor element, a voltage stabilizing circuit and a power supply; the heating layer is connected with the discharge end of the power supply; the semiconductor element of the temperature difference heating module at least comprises a cold end and a hot end, the hot end is arranged as the heat transfer layer, and the cold end is arranged as the outer skin of the wing to be heated; the semiconductor element of the temperature difference heating module is connected with the charging end of the power supply through the voltage stabilizing circuit; according to the invention, the semiconductor element of the temperature difference heating module is introduced into the anti-icing and deicing assembly, the heating layer is used as the hot end, the ambient environment is used as the cold end, and the thermoelectric effect is utilized to supply power to the anti-icing and deicing assembly; the ice coating of the airplane body is removed, and the flight safety of the airplane is ensured; the device has the characteristics of simple structure, energy conservation, environmental protection and the like, and can achieve the purpose of saving energy on the premise of meeting the requirement of preventing and removing ice.
Description
Technical Field
The invention belongs to the technical field of wing deicing, and particularly relates to a temperature difference power generation device for a wing deicing component, the deicing component and a method.
Background
The aircraft can face complex meteorological conditions in the process of flying at high altitude, particularly in wet and cold areas in winter, so that the windward part of the aircraft body, such as the front edge parts of wings, tail wings and engine air inlet channels, is easy to freeze; icing not only increases the weight of the aircraft, but also changes the aerodynamic performance of the aircraft, increases flight resistance, and seriously threatens flight safety.
The inventor finds that one mode in the wing ice prevention and removal is that the electric heating type ice prevention/removal component embeds the heating element into the structure which is easy to freeze of the airplane, and the electric heating type ice prevention/removal component is used for preventing/removing ice in an electrifying heating mode; although the anti-icing/deicing mode has high working efficiency, the energy consumption is high.
Disclosure of Invention
The invention provides a temperature difference power generation device for an anti-icing and deicing assembly of a wing, the anti-icing and deicing assembly and a method, which aim to solve the problems.
In order to achieve the above object, in a first aspect, the present invention provides a thermoelectric power generation device for an anti-icing wing assembly, which adopts the following technical solutions:
a thermoelectric generation device for a wing anti-icing assembly, comprising: the temperature difference heating module comprises a thermal insulation layer, a heating layer, a heat transfer layer and a temperature difference heating module semiconductor element which are sequentially attached;
the semiconductor element of the temperature difference heating module at least comprises a cold end and a hot end, the hot end is arranged as the heat transfer layer, and the cold end is arranged as the outer skin of the wing to be heated.
Furthermore, a plurality of P-type semiconductors and N-type semiconductors which are sequentially in cross connection are arranged between the cold end and the hot end.
In order to achieve the above object, in a second aspect, the present invention further provides an anti-icing and deicing assembly for a wing, which adopts the following technical solutions:
the wing ice preventing and removing assembly comprises a thermal insulation layer, a heating layer, a heat transfer layer, a temperature difference heating module semiconductor element, a voltage stabilizing circuit and a power supply, wherein the thermal insulation layer, the heating layer and the heat transfer layer are sequentially attached to each other;
the heating layer is connected with the discharge end of the power supply;
the semiconductor element of the temperature difference heating module at least comprises a cold end and a hot end, the hot end is arranged as the heat transfer layer, and the cold end is arranged as the outer skin of the wing to be heated;
the semiconductor element of the temperature difference heating module is connected with the charging end of the power supply through the voltage stabilizing circuit.
Furthermore, a plurality of P-type semiconductors and N-type semiconductors which are sequentially in cross connection are arranged between the cold end and the hot end.
Further, still include the controller, and with the detector that freezes that the controller is connected, the power with starting switch between the zone of heating with the controller is connected.
Furthermore, the controller is also connected with a temperature sensor, and the icing detector and the temperature sensor are used for detecting the surface condition of the wing.
Further, the controller is used for controlling the heating layer to be connected with the power supply when the temperature of the surface of the wing is less than 0 ℃ or the leading edge of the wing is coated with ice; and when the icing is detected to melt or the temperature of the surface of the wing is detected to be higher than a preset value, stopping electrifying the heating layer.
Further, the power supply is a storage battery, and the controller is a PLC.
In order to achieve the above object, in a third aspect, the present invention further provides a thermoelectric power generation method for an anti-icing wing assembly, which adopts the following technical scheme:
a thermoelectric power generation method for a wing anti-icing component adopts the thermoelectric power generation device for the wing anti-icing component, which comprises the following steps: the semiconductor element of the temperature difference heating module generates electricity by utilizing the temperature difference between the heat transfer layer and the outer skin.
In order to achieve the above object, in a fourth aspect, the present invention further provides a method for preventing and removing ice on a wing, which adopts the following technical scheme:
a method of deicing a wing using an airfoil deicing assembly according to the second aspect, comprising:
in the flying process of the airplane, the temperature sensor and the icing detector work periodically;
when a temperature sensor on the wing detects that the surface temperature of the wing is less than 0 ℃, or an icing detector detects that the front edge of the wing is coated with ice, the heating layer is connected with a power supply, and when the temperature difference between the cold end and the hot end of the temperature difference heating module semiconductor element is greater than a first preset value, the temperature difference heating module semiconductor element supplies power to the heating layer together with the power supply through a voltage stabilizing circuit; when the icing detector does not detect icing or the surface temperature of the wing is higher than a second preset value, the heating layer is stopped to be electrified, and the semiconductor element of the temperature difference heating module stores energy generated by the residual temperature difference in the power supply.
Compared with the prior art, the invention has the beneficial effects that:
according to the invention, the semiconductor element of the temperature difference heating module is introduced into the anti-icing and deicing assembly, the heating layer is used as the hot end, the ambient environment is used as the cold end, and the thermoelectric effect is utilized to supply power to the anti-icing and deicing assembly; the ice coating of the airplane body is removed, and the flight safety of the airplane is ensured; the device has the characteristics of simple structure, energy conservation, environmental protection and the like, and can achieve the purpose of saving energy on the premise of meeting the requirement of preventing and removing ice.
Drawings
The accompanying drawings, which form a part hereof, are included to provide a further understanding of the present embodiments, and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the present embodiments and together with the description serve to explain the present embodiments without unduly limiting the present embodiments.
FIG. 1 is a schematic structural view of example 1 of the present invention;
fig. 2 is a schematic structural view of a semiconductor element of a thermoelectric heating module according to embodiment 1 of the present invention;
FIG. 3 is a flowchart of the operation of embodiment 2 of the present invention;
FIG. 4 is a ladder diagram for PLC control according to embodiment 2 of the present invention;
the thermal insulation structure comprises a thermal insulation layer 1, a heating layer 2, a heating layer 3, a heat transfer layer 4, an outer skin 5, a temperature difference heating module semiconductor element 6 and a wing.
The specific implementation mode is as follows:
the invention is further described with reference to the following figures and examples.
It should be noted that the following detailed description is exemplary and is intended to provide further explanation of the disclosure. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.
Example 1:
as shown in fig. 1 and 2, the present embodiment provides a thermoelectric power generation device for an anti-icing assembly of a wing, including: the device comprises a heat insulation layer 1, a heating layer 2, a heat transfer layer 3 and a temperature difference heating module semiconductor element 5 which are sequentially attached;
the semiconductor element 5 of the temperature difference heating module at least comprises a cold end and a hot end, the hot end is arranged as the heat transfer layer 3, and the cold end is arranged as the outer skin 4 of the wing to be heated.
As shown in fig. 2, in this embodiment, a plurality of P-type semiconductors and N-type semiconductors are sequentially and cross-connected between the cold side and the hot side.
Example 2:
the embodiment provides a wing ice preventing and removing assembly, which comprises a heat insulation layer 1, a heating layer 2, a heat transfer layer 3, a temperature difference heating module semiconductor element 4, a voltage stabilizing circuit and a power supply, wherein the heat insulation layer, the heating layer 2 and the heat transfer layer 3 are sequentially attached to each other;
the heating layer 1 is connected with the discharge end of the power supply; the power supply can be arranged inside the wing or inside the cabin according to actual requirements and conditions;
the semiconductor element 5 of the temperature difference heating module is embedded into the anti-icing and deicing component, specifically, in the embodiment, the semiconductor element 5 of the temperature difference heating module at least comprises a cold end and a hot end, the hot end is arranged as the heat transfer layer 3, and the cold end is arranged as the outer skin 4 of the wing to be heated; in other embodiments, a cold end and a hot end which are independent can be arranged, wherein the cold end is contacted with the inner surface of the outer skin, and the hot end is contacted with the surface of the heating pad; the anti-icing component is organically combined with the thermoelectric generation element, so that the high-efficiency utilization of energy is realized;
the temperature difference heating module semiconductor element 5 is connected with the charging end of the power supply through the voltage stabilizing circuit; and in the initial temperature rise stage, the voltage stabilizing circuit provides stable voltage.
In this embodiment, the heat transfer layer 3 may be formed by compounding epoxy resin, glass fiber and graphene, the doping of the graphene in the heat transfer layer 3 improves the heat transfer capability of the composite material, and the doping of the glass fiber improves the strength of the composite material; the heat insulation layer 1 is formed by compounding epoxy resin and glass fiber; and an icing detector and a temperature sensor are arranged on the surface of the outer skin 4, and the icing and temperature change conditions on the surface of the wing are detected at regular time.
In this embodiment, a plurality of P-type semiconductors and N-type semiconductors which are sequentially cross-connected are disposed between the cold end and the hot end; in other embodiments, a conventional or existing thermoelectric generator may be used according to the requirement, and will not be described in detail herein.
In this embodiment, the wing ice and ice preventing and removing assembly further includes a controller, and an icing detector connected to the controller, and a start switch between the power supply and the heating layer 2 is connected to the controller; the heating layer is an electric heating layer; the icing detector is arranged on the surface of the outer skin 4 or at a corresponding position of an airplane shell and the like according to requirements by using an existing product; the thermoelectric heating module semiconductor element 5 is connected with the controller.
In this embodiment, the controller is further connected with a temperature sensor, and the icing detector and the temperature sensor are used for detecting the surface condition of the wing; the temperature sensor is arranged on the outer skin of the wing or on the outer surface of the wing.
In this embodiment, the controller is configured to control the heating layer to switch on the power supply when the temperature of the surface of the wing is less than 0 ℃ or the leading edge of the wing is iced; and when the icing is detected to melt or the temperature of the surface of the wing is detected to be higher than a preset value, stopping electrifying the heating layer.
In this embodiment, the power source is a battery, and the controller is a PLC.
As shown in fig. 4, the relay in the PLC is opened and closed in time according to each signal, specifically, the relay 01 is closed when the surface temperature of the outer skin 4 is less than 0 ℃, or is opened; the relay 02 is closed when the outer skin is frozen, or is opened; the relay 03 is closed when the temperature difference between the cold end and the hot end is less than 20 ℃, the heating layer is connected with a high-power supply, and otherwise, the relay is disconnected; the relay 04 is closed when the temperature difference between the cold end and the hot end is more than 20 ℃, the semiconductor element 5 of the temperature difference heating module is connected with the heating pad, and otherwise, the relay is disconnected; the relay 05 is normally open when the heating layer is connected with a low-power supply; the relay 07 is closed when no ice is coated on the surface of the outer skin, or is opened; when the temperature difference between the cold end and the hot end of the relay 08 is more than 10 ℃, the relay is closed, the semiconductor element 5 of the temperature difference heating module is connected with a power supply, and otherwise, the relay is disconnected; the cold end and the hot end can be provided with temperature sensors for temperature detection;
it should be noted that the high-power supply referred to in this embodiment refers to a power supply state corresponding to the situation of the thermoelectric generation application; the low-power supply refers to the power supply state corresponding to the thermoelectric power generation condition.
The working principle or process of the embodiment is as follows:
as shown in fig. 3, the temperature sensor 7 and the icing detector 6 operate periodically while the aircraft is in flight. When the temperature sensor 7 on the wing detects that the surface temperature of the wing is less than 0 ℃ or the icing detector 6 finds that the front edge of the wing is iced, the electric heating layer 2 of the anti-icing/deicing assembly is connected with a power supply (high power), and when the temperature difference between the cold end and the hot end of the thermoelectric generator 5 is more than 20 ℃, the thermoelectric generator 5 and the power supply (low power) jointly supply power to the electric heating layer 2 of the anti-icing/deicing assembly through the voltage stabilizing circuit 8. When the icing detector 6 detects icing or the temperature of the surface of the wing is higher than 5 ℃, the electrification of the electric heating layer is stopped, and the thermoelectric generator 5 stores energy generated by the residual temperature difference in the storage battery 9 for other equipment of the airplane to use.
The embodiment does not consume any fuel and generate any waste material in the power generation process; the device has small volume and light weight, and can not generate additional influence on the weight of the airplane; the device can carry out secondary utilization on the heat generated by the anti-icing/deicing assembly, thereby improving the utilization rate of energy; the thermoelectric generator is embedded into the anti-icing and deicing assembly, and the structure is simple.
Example 3:
the embodiment provides a thermoelectric power generation method for a wing anti-icing component, which adopts the thermoelectric power generation device for the wing anti-icing component as described in embodiment 1, and specifically comprises the following steps: the semiconductor element of the temperature difference heating module generates electricity by utilizing the temperature difference between the heat transfer layer and the outer skin.
Example 4:
this embodiment provides a method for preventing and removing ice on a wing, which uses the wing ice-preventing and removing assembly as described in embodiment 2, and includes:
in the flying process of the airplane, the temperature sensor and the icing detector work periodically;
when a temperature sensor on the wing detects that the surface temperature of the wing is less than 0 ℃, or an icing detector detects that the front edge of the wing is coated with ice, the heating layer is connected with a power supply, and when the temperature difference between the cold end and the hot end of the temperature difference heating module semiconductor element is greater than a first preset value, the temperature difference heating module semiconductor element supplies power to the heating layer together with the power supply through a voltage stabilizing circuit; when the icing detector does not detect icing or the surface temperature of the wing is higher than a second preset value, the heating layer is stopped to be electrified, and the semiconductor element of the temperature difference heating module stores energy generated by the residual temperature difference in the power supply.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and those skilled in the art can make various modifications and variations. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present embodiment should be included in the protection scope of the present embodiment.
Claims (10)
1. A thermoelectric generation device for wing anti-icing subassembly, its characterized in that includes: the temperature difference heating module comprises a thermal insulation layer, a heating layer, a heat transfer layer and a temperature difference heating module semiconductor element which are sequentially attached;
the semiconductor element of the temperature difference heating module at least comprises a cold end and a hot end, the hot end is arranged as the heat transfer layer, and the cold end is arranged as the outer skin of the wing to be heated.
2. The thermoelectric generation device for an anti-icing wing assembly as defined in claim 1, wherein a plurality of P-type semiconductors and N-type semiconductors are sequentially cross-connected between the cold end and the hot end.
3. The wing anti-icing component is characterized by comprising a thermal insulation layer, a heating layer, a heat transfer layer, a temperature difference heating module semiconductor element, a voltage stabilizing circuit and a power supply which are sequentially attached;
the heating layer is connected with the discharge end of the power supply;
the semiconductor element of the temperature difference heating module at least comprises a cold end and a hot end, the hot end is arranged as the heat transfer layer, and the cold end is arranged as the outer skin of the wing to be heated;
the semiconductor element of the temperature difference heating module is connected with the charging end of the power supply through the voltage stabilizing circuit.
4. The airfoil anti-icing assembly of claim 3, wherein a plurality of sequentially cross-connected P-type and N-type semiconductors are disposed between the cold end and the hot end.
5. The airfoil anti-icing assembly of claim 3, further comprising a controller, and an icing detector coupled to the controller, wherein an activation switch between the power source and the heating layer is coupled to the controller.
6. The wing assembly according to claim 5, wherein the controller is further coupled to a temperature sensor, the ice detector and the temperature sensor for detecting a surface condition of the wing.
7. The wing ice and ice protection assembly of claim 6, wherein the controller is configured to control the heating layer to turn on the power supply when the wing surface temperature is less than 0 ℃ or the wing leading edge is iced; and when the icing is detected to melt or the temperature of the surface of the wing is detected to be higher than a preset value, stopping electrifying the heating layer.
8. The wing assembly according to claim 5, wherein the power source is a battery and the controller is a PLC.
9. The thermoelectric power generation method for the wing anti-icing component is characterized in that the thermoelectric power generation device for the wing anti-icing component as claimed in any one of claims 1 to 2 is adopted, and specifically the method comprises the following steps: the semiconductor element of the temperature difference heating module generates electricity by utilizing the temperature difference between the heat transfer layer and the outer skin.
10. A method for deicing an airfoil, characterized in that an airfoil assembly according to any one of claims 3 to 8 is used, comprising:
in the flying process of the airplane, the temperature sensor and the icing detector work periodically;
when a temperature sensor on the wing detects that the surface temperature of the wing is less than 0 ℃, or an icing detector detects that the front edge of the wing is coated with ice, the heating layer is connected with a power supply, and when the temperature difference between the cold end and the hot end of the temperature difference heating module semiconductor element is greater than a first preset value, the temperature difference heating module semiconductor element supplies power to the heating layer together with the power supply through a voltage stabilizing circuit; when the icing detector does not detect icing or the surface temperature of the wing is higher than a second preset value, the heating layer is stopped to be electrified, and the semiconductor element of the temperature difference heating module stores energy generated by the residual temperature difference in the power supply.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210085662.8A CN114435597B (en) | 2022-01-25 | 2022-01-25 | Thermoelectric power generation device for wing deicing component, deicing component and method |
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| CN202210085662.8A CN114435597B (en) | 2022-01-25 | 2022-01-25 | Thermoelectric power generation device for wing deicing component, deicing component and method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115599144A (en) * | 2022-12-12 | 2023-01-13 | 中国空气动力研究与发展中心低速空气动力研究所（Cn） | Dynamic temperature feedback electric heating anti-icing method and device for air inlet passage |
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| CN114435597B (en) | 2024-04-26 |
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