CN110963044A - Wing ice preventing and removing device based on nano composite phase change material and working method thereof - Google Patents
Wing ice preventing and removing device based on nano composite phase change material and working method thereof Download PDFInfo
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- CN110963044A CN110963044A CN201911345052.1A CN201911345052A CN110963044A CN 110963044 A CN110963044 A CN 110963044A CN 201911345052 A CN201911345052 A CN 201911345052A CN 110963044 A CN110963044 A CN 110963044A
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- 239000012782 phase change material Substances 0.000 title claims abstract description 52
- 239000002114 nanocomposite Substances 0.000 title claims abstract description 41
- 238000000034 method Methods 0.000 title claims abstract description 10
- 239000002184 metal Substances 0.000 claims description 17
- 230000008859 change Effects 0.000 claims description 13
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 13
- 239000002105 nanoparticle Substances 0.000 claims description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 5
- 229910021389 graphene Inorganic materials 0.000 claims description 5
- 238000005485 electric heating Methods 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 4
- 239000005639 Lauric acid Substances 0.000 claims description 3
- 238000001914 filtration Methods 0.000 claims description 3
- 239000012535 impurity Substances 0.000 claims description 3
- 238000005728 strengthening Methods 0.000 claims description 2
- 239000012071 phase Substances 0.000 claims 3
- 239000000463 material Substances 0.000 claims 1
- 239000012074 organic phase Substances 0.000 claims 1
- 238000005265 energy consumption Methods 0.000 abstract description 3
- 238000005457 optimization Methods 0.000 description 5
- 238000004146 energy storage Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 230000002265 prevention Effects 0.000 description 3
- 239000002131 composite material Substances 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005507 spraying Methods 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
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/04—Hot gas application
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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
-
- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Resistance Heating (AREA)
Abstract
The invention discloses a wing ice preventing and removing device based on a nano composite phase change material and a working method thereof. According to the invention, the engine is adopted to bleed air, and the air is filtered and dried and then is introduced into the inner flow channel of the wing, the air and the closed cavity layer exchange heat through thermal convection, and the nano composite phase change material in the closed cavity layer is heated, so that the redundant heat can be stored in the wing more quickly, and the icing on the surface of the wing is effectively prevented. Meanwhile, the electrothermal deicing component works when latent heat is insufficient, so that the device has the characteristics of strong reliability, high deicing efficiency, low energy consumption and the like.
Description
Technical Field
The invention relates to the technical field of airplane anti-icing and deicing, in particular to a wing anti-icing and deicing device based on a nano composite phase change material and a working method thereof.
Background
Icing of the flying wing is a serious hazard, which destroys the aerodynamic flow field on the surface of the wing of the aircraft, increases the flight resistance, reduces the lift force of the wing, and as the power for compensating the extra resistance increases and the flight angle of attack increases due to the nose lifting adopted for maintaining the height, the critical angle of attack decreases, the aircraft can stall at a higher speed or a lower angle of attack than normal, and the maneuverability and the stability deteriorate, thereby causing serious flight accidents.
The current common deicing prevention and removal technologies can be divided into gas-heating deicing prevention and removal and electric-heating deicing prevention and removal according to working modes. The aerothermal deicing refers to the spraying of high-temperature and high-pressure air flow extracted from an aircraft engine in an anti-icing cavity through an air-entraining pipe, so that the temperature of the outer surface of the wing is kept above 10 ℃; the electrothermal deicing and preventing component is directly placed on the inner surface of the front edge of the wing to deice, has small volume and simple structure, can be automatically controlled, has larger energy consumption for electrothermal deicing and preventing, and increases the fuel compensation loss of the airplane.
The phase change energy storage technology can adjust mismatching of energy supply and demand in time and space, and is an effective way for improving energy utilization efficiency. The phase change energy storage has the advantages of compact structural design, high energy storage density and approximately isothermal phase change process. However, most phase change materials have low thermal conductivity, which limits the heat transfer efficiency during the phase change process on the ground and in space. The nano-particles are added into the traditional phase-change material to form the nano-fluid composite phase-change material, so that the nano-fluid composite phase-change material has the potential of enhancing the heat transfer of the phase-change material and improving the efficiency of an energy storage system. The graphene has the characteristics of high heat conductivity coefficient and large specific surface area, and the addition of the graphene nanoparticles into the phase-change material is beneficial to improving the heat transfer performance of the phase-change material.
Disclosure of Invention
The invention aims to solve the technical problem of providing an anti-deicing device for wings based on a nano composite phase change material and a working method thereof aiming at the defects involved in the background technology.
The invention adopts the following technical scheme for solving the technical problems:
the wing ice preventing and removing device based on the nano composite phase change material comprises a gas compressor, a stop valve, a filter, a dryer, an inner wing flow channel, an electric heating ice removing assembly, a first temperature sensor, an icing detector, a metal fin, a second temperature sensor, a water separator, a flow valve and a controller;
the outlet of the compressor, the stop valve, the filter and the inlet of the dryer are connected in sequence through pipelines; the inlet of the compressor is connected with the air-entraining part of the engine;
the filter (3) is used for filtering impurities in engine bleed air; the dryer (4) is used for removing moisture in the pressurized bleed air;
the inner surface of the outer skin of the wing of the airplane is provided with a heat-conducting closed cavity layer, and the closed cavity layer is uniformly divided into a plurality of closed cavities; an inner wing flow channel is formed between the closed cavity layer and the inner wing skin;
one end of an inner wing runner of the airplane is connected with an outlet of the dryer through a pipeline, and the other end of the inner wing runner of the airplane is connected with a gas inlet pipeline of the water separator; one end of the flow valve is connected with a gas outlet pipeline of the water separator, and the other end of the flow valve is communicated with the external atmosphere;
the nano composite phase change material is filled in each closed cavity;
the electrothermal deicing assembly is arranged in the closed cavity layer and comprises a plurality of heaters which are uniformly arranged on the inner surface of the outer skin of the wing of the airplane;
the first temperature sensor and the icing detector are both arranged on the surface of the outer skin of the wing, and the second temperature sensor is arranged at an outlet of the inner runner of the wing;
the controller is respectively electrically connected with the first temperature sensor, the icing detector, the second temperature sensor, the stop valve, the flow valve and each heater and is used for controlling the stop valve, the flow valve and each heater to work according to the sensing data of the first temperature sensor, the icing detector and the second temperature sensor.
As a further optimization scheme of the wing ice preventing and removing device based on the nano-composite phase-change material, the nano-composite phase-change material is prepared by mixing a dodecanol-lauric acid organic phase-change material and graphene nanoparticles.
As a further optimization scheme of the wing ice preventing and removing device based on the nano-composite phase-change material, the phase-change temperature of the nano-composite phase-change material is 15 ℃.
As a further optimization scheme of the wing ice preventing and removing device based on the nano-composite phase change material, a plurality of metal fins are uniformly arranged on the surface of the closed cavity layer close to the wing inner flow channel, one ends of the metal fins are arranged in the closed cavity layer, and the other ends of the metal fins extend out of the closed cavity layer and extend into the wing inner flow channel and are used for strengthening heat convection and heat conduction.
The invention also discloses a working method of the wing ice preventing and removing device based on the nano composite phase change material, which comprises the following steps:
step 1), pressurizing engine bleed air through a compressor, enabling the engine bleed air to flow through a stop valve, a filter and a dryer, then enabling the engine bleed air to enter an inner flow channel of a wing to exchange heat with a closed cavity layer through thermal convection, and enabling metal fins to enhance thermal convection heat transfer; the heat is transferred into the closed cavity layer and absorbed and stored as phase change latent heat by the nano composite phase change material;
step 2), when the first temperature sensor monitors that the temperature of the surface of the wing is too low, the nano composite phase change material is stored to begin to release phase change latent heat for heating the surface of the wing, and hot gas is subjected to full heat exchange in an inner flow channel of the wing, then the temperature of the hot gas is reduced, and the hot gas flows through a water separator and a flow valve and enters the atmosphere;
and 3) when the second temperature sensor monitors that the temperature of hot gas at the outlet of the flow channel in the wing is too low or the icing detector detects that the surface of the wing is iced, the controller controls the heaters to work to directly heat the surface of the wing, and meanwhile, redundant heat is stored in the nano composite phase change material of the closed cavity layer.
Compared with the prior art, the invention adopting the technical scheme has the following technical effects:
according to the invention, the engine is adopted to bleed air, and the air is filtered and dried and then is introduced into the inner flow channel of the wing, the air and the sealed cavity layer exchange heat through thermal convection, the nano composite phase change material in the sealed cavity layer is heated, and the addition of the metal fin strengthens the thermal convection, so that the redundant heat can be stored in the wing more quickly, and the icing on the surface of the wing is effectively prevented. Meanwhile, the nano composite phase change material absorbs a large amount of phase change latent heat when the airplane stays on the ground, and the nano particles with high heat conductivity are added into the phase change material, so that the heat conduction between the surface of the wing and the phase change material is improved, and the temperature of the surface of the wing is not lower than the freezing point. The working mode of preventing and removing ice of the wings is automatically adjusted through the controller, so that the device has the characteristics of strong reliability, high ice preventing and removing efficiency, low energy consumption and the like.
Drawings
FIG. 1 is a schematic view of a wing deicing and ice preventing device made of a nanocomposite phase-change material.
The device comprises a compressor, a stop valve, a filter, a dryer, an outer wing skin, an inner wing skin, a runner, a closed cavity layer, an electrothermal deicing component, a first temperature sensor, an icing detector, a metal fin, a second temperature sensor, a water separator, a flow valve and a controller, wherein the compressor is 1, the stop valve is 2, the filter is 3, the dryer is 4, the outer wing skin is 5, the inner wing skin is 6, the inner wing channel is 7, the closed cavity layer is 8, the electrothermal deicing component is 9, the first temperature sensor is 10, the icing detector is 11.
Detailed Description
The technical scheme of the invention is further explained in detail by combining the attached drawings:
the present invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, components are exaggerated for clarity.
As shown in fig. 1, the invention discloses a wing ice preventing and removing device based on a nano composite phase change material, which comprises a compressor 1, a stop valve 2, a filter 3, a dryer 4, a wing internal flow channel 7, an electric heating ice removing component 9, a first temperature sensor 10, an icing detector 11, a metal fin 12, a second temperature sensor 13, a water separator 14, a flow valve 15 and a controller 16;
the outlet of the compressor 1, the stop valve 2, the filter 3 and the inlet of the dryer 4 are connected in sequence through pipelines; an inlet of the compressor 1 is connected with an engine air-entraining part;
the filter (3) is used for filtering impurities in engine bleed air; the dryer (4) is used for removing moisture in the pressurized bleed air;
the inner surface of the outer wing skin 5 of the airplane is provided with a heat-conducting closed cavity layer 8 which is uniformly divided into a plurality of closed cavities; an inner wing flow channel 7 is formed between the closed cavity layer and the inner wing skin 6;
one end of an inner wing runner 7 of the airplane is connected with an outlet of the dryer 4 through a pipeline, and the other end of the inner wing runner is connected with a gas inlet pipeline of the water separator 14; one end of the flow valve 15 is connected with a gas outlet pipeline of the water separator 14, and the other end of the flow valve is communicated with the external atmosphere;
the nano composite phase change material is filled in each closed cavity;
the electrothermal deicing assembly 9 is arranged in the closed cavity layer 8 and comprises a plurality of heaters which are uniformly arranged on the inner surface of the outer skin 5 of the wing of the airplane;
the first temperature sensor 5 and the icing detector 9 are both arranged on the surface of the outer wing skin 5, and the second temperature sensor 13 is arranged at an outlet of the inner wing runner 7;
the controller 16 is electrically connected with the first temperature sensor 5, the icing detector 9, the second temperature sensor 13, the stop valve 2, the flow valve 15 and the heaters respectively and is used for controlling the stop valve 2, the flow valve 15 and the heaters to work according to the sensing data of the first temperature sensor 5, the icing detector 9 and the second temperature sensor 13.
As a further optimization scheme of the wing ice preventing and removing device based on the nano-composite phase-change material, the nano-composite phase-change material is prepared by mixing a dodecanol-lauric acid organic phase-change material and graphene nanoparticles.
As a further optimization scheme of the wing ice preventing and removing device based on the nano-composite phase-change material, the phase-change temperature of the nano-composite phase-change material is 15 ℃.
As a further optimized scheme of the wing ice preventing and removing device based on the nano-composite phase change material, a plurality of metal fins 12 are uniformly arranged on the surface of the closed cavity layer 8 close to the wing inner flow channel 7, one end of each metal fin is arranged in the closed cavity layer 8, and the other end of each metal fin extends out of the closed cavity layer 8 and extends into the wing inner flow channel 7 to strengthen heat convection and heat conduction.
The invention also discloses a working method of the wing ice preventing and removing device based on the nano composite phase change material, which comprises the following steps:
step 1, pressurizing engine bleed air through an air compressor 1, enabling the engine bleed air to flow through a stop valve 2, a filter 3 and a dryer 4, then enabling the engine bleed air to enter an inner wing flow channel 7 to exchange heat with a closed cavity layer 8 through thermal convection, and enabling metal fins to strengthen thermal convection heat transfer; the heat is transferred into the closed cavity layer 8 and absorbed and stored as phase change latent heat by the nano composite phase change material;
step 2, when the first temperature sensor 5 monitors that the temperature of the surface of the wing is too low, the nano composite phase change material is stored to begin to release phase change latent heat for heating the surface of the wing, and hot gas is subjected to sufficient heat exchange in the wing internal flow channel 7, then the temperature is reduced, and the hot gas flows through the water separator 14 and the flow valve 15 and enters the atmosphere;
and 3, when the second temperature sensor 13 monitors that the temperature of hot gas at the outlet of the flow channel 7 in the wing is too low or the icing detector 9 detects that the surface of the wing is iced, the controller 16 controls the heaters to work to directly heat the surface of the wing, and meanwhile, redundant heat is stored in the nano composite phase change material of the closed cavity layer 8.
It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein, including technical and scientific terms), have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
The above-mentioned embodiments, objects, technical solutions and advantages of the present invention are further described in detail, it should be understood that the above-mentioned embodiments are only illustrative of the present invention and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. The wing ice preventing and removing device based on the nano composite phase change material is characterized by comprising a gas compressor (1), a stop valve (2), a filter (3), a dryer (4), a wing inner flow channel (7), an electric heating ice removing assembly (9), a first temperature sensor (10), an icing detector (11), a metal fin (12), a second temperature sensor (13), a water separator (14), a flow valve (15) and a controller (16);
the outlet of the compressor (1), the stop valve (2), the filter (3) and the inlet of the dryer (4) are connected in sequence through pipelines; an inlet of the compressor (1) is connected with an engine air-entraining part;
the filter (3) is used for filtering impurities in engine bleed air; the dryer (4) is used for removing moisture in the pressurized bleed air;
the inner surface of the outer wing skin (5) of the airplane is provided with a heat-conducting closed cavity layer (8), and the closed cavity layer is uniformly divided into a plurality of closed cavities; an inner wing flow channel (7) is formed between the closed cavity layer and the inner wing skin (6);
one end of an inner wing runner (7) of the airplane is connected with an outlet of the dryer (4) through a pipeline, and the other end of the inner wing runner is connected with a gas inlet pipeline of the water separator (14); one end of the flow valve (15) is connected with a gas outlet pipeline of the water separator (14), and the other end of the flow valve is communicated with the outside atmosphere;
the nano composite phase change material is filled in each closed cavity;
the electrothermal deicing assembly (9) is arranged in the closed cavity layer (8) and comprises a plurality of heaters which are uniformly arranged on the inner surface of the outer skin (5) of the wing of the airplane;
the first temperature sensor (5) and the icing detector (9) are both arranged on the surface of the outer wing skin (5), and the second temperature sensor (13) is arranged at an outlet of the inner wing runner (7);
the controller (16) is respectively electrically connected with the first temperature sensor (5), the icing detector (9), the second temperature sensor (13), the stop valve (2), the flow valve (15) and the heaters and is used for controlling the stop valve (2), the flow valve (15) and the heaters to work according to the sensing data of the first temperature sensor (5), the icing detector (9) and the second temperature sensor (13).
2. The wing ice and ice protection device based on the nano-composite phase change material as claimed in claim 1, wherein the nano-composite phase change material is prepared by mixing a dodecanol-lauric acid organic phase change material with graphene nanoparticles.
3. The device of claim 2, wherein the nanocomposite phase change material has a phase change temperature of 15 ℃.
4. The wing ice preventing and removing device based on the nano composite phase change material as claimed in claim 1, wherein a plurality of metal fins (12) are uniformly arranged on the surface of the closed cavity layer (8) close to the wing inner flow channel (7), one end of each metal fin is arranged in the closed cavity layer (8), and the other end of each metal fin extends out of the closed cavity layer (8) and extends into the wing inner flow channel (7) for strengthening heat convection and heat conduction.
5. The method for operating the wing deicing device based on the nanocomposite phase change material as claimed in claim 1, comprising the following steps:
step 1), pressurizing engine bleed air through an air compressor (1), enabling the engine bleed air to flow through a stop valve (2), a filter (3) and a dryer (4), then enabling the engine bleed air to enter an inner wing flow channel (7) to exchange heat with a closed cavity layer (8) through thermal convection, and enabling metal fins to strengthen thermal convection heat transfer; the heat is transferred into the closed cavity layer (8) and absorbed and stored as phase change latent heat by the nano composite phase change material;
step 2), when the first temperature sensor (5) monitors that the temperature of the surface of the wing is too low, the nano composite phase change material is stored to begin to release phase change latent heat for heating the surface of the wing, and hot gas is subjected to full heat exchange in the wing inner flow channel (7), then the temperature is reduced, and the hot gas flows through the water separator (14) and the flow valve (15) and enters the atmosphere;
and 3) when the second temperature sensor (13) monitors that the temperature of hot gas at the outlet of the flow channel (7) in the wing is too low or the icing detector (9) detects that the surface of the wing is iced, the controller (16) controls the heaters to work to directly heat the surface of the wing, and meanwhile, redundant heat is stored in the nano composite phase change material of the closed cavity layer (8).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911345052.1A CN110963044B (en) | 2019-12-24 | 2019-12-24 | Wing deicing device based on nanocomposite phase change material and working method thereof |
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| CN201911345052.1A CN110963044B (en) | 2019-12-24 | 2019-12-24 | Wing deicing device based on nanocomposite phase change material and working method thereof |
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| CN114435597A (en) * | 2022-01-25 | 2022-05-06 | 山东大学 | Temperature difference power generation device for wing anti-icing and deicing assembly, anti-icing and deicing assembly and method |
| CN114834641A (en) * | 2022-03-29 | 2022-08-02 | 山东大学 | Anti-icing and deicing device based on phase change energy storage and aircraft |
| EP4124573A1 (en) * | 2021-07-29 | 2023-02-01 | Airbus Defence and Space GmbH | Ice protection system and method for an aircraft component, aircraft compo-nent and aircraft using such a system |
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|---|---|
| CN110963044B (en) | 2024-02-13 |
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