CN116374176A - Anti-icing and deicing device and anti-icing and deicing method for aircraft - Google Patents
Anti-icing and deicing device and anti-icing and deicing method for aircraft Download PDFInfo
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- CN116374176A CN116374176A CN202310159039.7A CN202310159039A CN116374176A CN 116374176 A CN116374176 A CN 116374176A CN 202310159039 A CN202310159039 A CN 202310159039A CN 116374176 A CN116374176 A CN 116374176A
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- icing
- layer
- aircraft
- deicing
- temperature
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- 238000000034 method Methods 0.000 title claims abstract description 17
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 43
- 239000000956 alloy Substances 0.000 claims abstract description 43
- 229910001285 shape-memory alloy Inorganic materials 0.000 claims abstract description 9
- 238000010438 heat treatment Methods 0.000 claims description 13
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical group [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 claims description 8
- 239000002042 Silver nanowire Substances 0.000 claims description 7
- 238000001816 cooling Methods 0.000 claims description 4
- 230000002265 prevention Effects 0.000 claims description 3
- 239000010410 layer Substances 0.000 description 86
- 230000015572 biosynthetic process Effects 0.000 description 7
- 230000006870 function Effects 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 239000011248 coating agent Substances 0.000 description 3
- 238000000576 coating method Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000000151 deposition Methods 0.000 description 2
- 230000002209 hydrophobic effect Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000011017 operating method Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 239000011247 coating layer Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000003446 memory effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 239000004332 silver Substances 0.000 description 1
- 230000003075 superhydrophobic effect Effects 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
- 238000002834 transmittance Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
An anti-icing and deicing device for an aircraft and an anti-icing and deicing method using the same, capable of effectively preventing and rapidly icing without generating electromagnetic interference while minimizing the generation of additional resistance and additional power. An aircraft anti-icing and deicing device comprising: a bottom heated layer secured to the flight element; a middle alloy skeleton provided on the upper portion of the bottom layer heated layer and made of a shape memory alloy, and capable of deforming or recovering deformation according to the temperature of the bottom layer heated layer; and a top layer of elastic paper-cut layer which is arranged on the upper part of the middle layer alloy skeleton and is connected with the middle layer alloy skeleton in a mode of being capable of elastically deforming along with the deformation of the middle layer alloy skeleton.
Description
Technical Field
The invention relates to an anti-icing and deicing device for an aircraft and an anti-icing and deicing method for the aircraft.
Background
It is known that during flight of an aircraft, such as an aircraft, icing can occur in certain parts of the aircraft due to the very low temperature of the external environment. Such locations include, for example, wing and tail leading edges, propeller leading edges, inlet duct leading edges, cockpit windshields, and the like. If severe icing occurs at the location, then flight may be dangerous. For example, icing of the leading edges of wings and tails may change the profile shape of the wing, reduce lift, increase drag, and even make flight maneuvers difficult and unstable, and icing in other areas can present various difficulties. Accordingly, in order to prevent ice formation at certain portions of the surface of the aircraft or to remove ice layers during ice formation, anti-icing and deicing devices or mechanisms are typically provided at such portions of the aircraft.
As a method for preventing and removing ice, patent document 1 (CN 202011308575.1) discloses a novel anti-ice coating for an aircraft composite wing and a method for preparing the same, and the anti-ice coating is made of a hydrophobic bottom layer, a super-hydrophobic surface layer, and the like. As another method, patent document 2 (CN 202011073742.9) discloses an electrically heated coating for preventing and removing ice of a wing, which is made by electrically heating. As another method, patent document 3 (CN 202111462898.0) discloses a wing plasma stall prevention/ice control dual-mode switching system and an operating method, which uses plasma discharge to prevent and remove ice from flowing in an airfoil, and patent document 4 (CN 201910786866.2) discloses an operating method for removing ice from the surface of an aircraft by using a memory alloy, wherein deformation occurs by sensing temperature change of the memory alloy, and ice layers are mutually extruded and removed for deicing.
Prior art literature
Patent literature
Patent document 1: CN202011308575.1
Patent document 2: CN202011073742.9
Patent document 3: CN202111462898.0
Patent document 4: CN201910786866.2
Disclosure of Invention
Technical problem to be solved by the invention
However, the method for preventing and removing ice based on the hydrophobic coating layer employed in patent document 1 has a limited range of application, and there is an adverse effect that additional resistance is generated in the case where the anti-ice and the ice removing are not required. The electric heating type deicing/anti-icing device disclosed in patent document 2 has the disadvantages of high power consumption and slow response. Further, the method for controlling ice by plasma discharge employed in patent document 3 has a disadvantage of large power consumption, and also has a disadvantage of generating strong electromagnetic interference due to the need of external high-voltage power supply, which is disadvantageous in communication between the aircraft and the ground control tower, and the like. Patent document 4 discloses a method of splicing only memory alloy, in which only two-dimensional ice layers are moved mutually, and the displacement and shape change of the ice layers are limited, so that the deicing effect is poor.
The present invention has been made to solve the above-mentioned problems, and an object of the present invention is to provide an anti-icing and deicing device for an aircraft and an anti-icing and deicing method using the same, which can effectively prevent ice and rapidly freeze without generating electromagnetic interference while minimizing the generation of additional resistance and additional power.
Technical proposal adopted for solving the technical problems
A first aspect of the present invention provides an anti-icing and deicing device for an aircraft, for anti-icing and deicing of a flight element of the aircraft, characterized by comprising:
a bottom heated layer secured to the flight element;
a middle alloy skeleton provided on the upper portion of the bottom layer heated layer and made of a shape memory alloy, and capable of deforming or recovering deformation according to the temperature of the bottom layer heated layer; and
the top layer elastic paper-cut layer is arranged on the upper portion of the middle layer alloy skeleton and is connected with the middle layer alloy skeleton in a mode of being capable of being elastically deformed along with deformation of the middle layer alloy skeleton.
A second aspect of the present invention is characterized by further comprising a heater for heating the underlying heated layer.
A third aspect of the present invention is characterized in that, on the basis of the second aspect, the heater is a silver nanowire heater.
A fourth technical aspect of the present invention provides an anti-icing and deicing method for an aircraft, using the anti-icing and deicing device for an aircraft according to any one of the first to third technical aspects to perform anti-icing and deicing on a flight component of the aircraft, the method being characterized by comprising:
determining whether there is an anti-icing demand or a de-icing demand; and
and in the case that the ice prevention requirement or the ice removal requirement is judged to exist, repeatedly heating and cooling the bottom heated layer for more than two times, so that the temperature of the middle laminated skeleton repeatedly changes between a temperature less than the memory temperature and a temperature greater than the memory temperature.
Effects of the invention
According to the aircraft anti-icing and deicing device of the first technical scheme, the shape memory characteristics of the middle-layer alloy skeleton formed by the shape memory alloy can be utilized for effective anti-icing and deicing. Specifically, the bottom layer heated layer is heated, and the heated bottom layer heated layer transmits heat to the middle alloy skeleton arranged on the upper portion until the temperature of the middle alloy skeleton exceeds the memory temperature of the middle alloy skeleton, so that the middle alloy skeleton is deformed, and the top layer elastic paper-cut layer arranged on the top portion is elastically deformed to bulge. Then, the bottom layer heated layer is cooled by stopping the heating to the bottom layer heated layer, so that the temperature of the intermediate alloy skeleton is lower than its memory temperature due to heat exchange, thereby returning to the original shape. Since the middle alloy skeleton is restored to the original shape, the top layer of the elastic scissor layer connected to the middle alloy skeleton is restored from the bulged state to the original state (i.e., elastic recovery occurs). Therefore, the middle layer laminated skeleton is repeatedly deformed and restored by repeatedly heating and cooling the bottom layer heated layer at least twice, so that the top layer elastic paper-cut layer attached with or about to be attached with ice is repeatedly swelled and restored. As a result, such deformation and recovery of deformation can break the ice layer, and the broken ice can be rapidly peeled off from the top elastic paper-cut layer by the air flow. Therefore, the anti-icing and deicing can be efficiently performed, no additional resistance is generated, the power consumption is low, and no electromagnetic interference is generated.
In addition, according to the aircraft anti-icing and deicing device of the third claim, as the heater, a silver nanowire heater is used. The silver nanowires have excellent light transmittance and flex resistance in addition to excellent conductivity of silver. By integrating silver nanowire heaters in a multilayer structure, temperature variations are induced by superimposing the heaters. By utilizing the temperature dependent resistance of the silver nanowire network as a process variable for the active control system, the limitation of the traditional heating mode that is difficult to apply to the variable appearance structure can be solved.
Drawings
FIG. 1 is a schematic view of an aircraft anti-icing de-icing assembly according to an embodiment of the present invention.
FIG. 2 is a schematic operational view of an aircraft anti-icing de-icing assembly of an embodiment of the present invention mounted to an airfoil component.
FIG. 3 is an anti-icing and deicing flow chart for an aircraft anti-icing and deicing device according to one embodiment of the present invention.
Symbol description
S anti-icing de-icing device (aircraft anti-icing de-icing device)
21 airfoil component
22 bottom heated layer
23 middle layer alloy skeleton
24 top layer elastic paper cutting layer
Detailed Description
First, a detailed configuration of an aircraft anti-icing and deicing device (hereinafter, simply referred to as an anti-icing and deicing device) S according to an embodiment of the present invention will be described with reference to fig. 1 to 2.
Fig. 1 shows an anti-icing de-icing device S according to an embodiment of the invention and an airfoil component 21 to which the anti-icing de-icing device S is mounted. The airfoil component 21 is, for example, a wing or tail of an aircraft, and the anti-icing and deicing device S mainly comprises a bottom heated layer 22, a middle alloy skeleton 23 and a top elastic scissor layer 24. The bottom heated layer 22, the middle alloy skeleton 23 and the top elastic scissor layer 24 are laminated and connected from bottom to top in this order to form the anti-icing and deicing device S.
Specifically, the bottom layer heated layer 22 is fixedly connected to the airfoil member 21, the middle alloy skeleton 23 is connected to the bottom layer heated layer 22 so as to be deformable according to the temperature of the bottom layer heated layer 22, and the top layer elastic scissor layer 23 is connected to the middle alloy skeleton 23 so as to be deformable according to the deformation of the middle alloy skeleton 23.
When the underlayer heated layer 22 is fixedly connected to the airfoil member 21, the underlayer heated layer 22 can be heated by a heater (not shown) that is also disposed on the airfoil member 21, and the heater may be an aircraft member that is originally disposed on the airfoil member 21 or may belong to the anti-icing/deicing device S. Further, preferably, the heater is a silver nanowire heater.
The middle alloy skeleton 23 is composed of a shape memory alloy having a prescribed memory temperature. That is, when the temperature of the middle alloy skeleton 23 exceeds the memory temperature, the middle alloy skeleton 23 is deformed, and when the temperature of the middle alloy skeleton 23 is lower than the memory temperature, the middle alloy skeleton 23 is restored to the original shape. In other words, the middle alloy skeleton 23 may be a shape memory alloy having a one-way memory effect, but is not limited thereto. For example, the initial configuration of middle alloy skeleton 23 is planar frame-like. After the bottom layer is heated by the heater 22, heat is transferred from the bottom layer by the heater 22 to the middle alloy skeleton 23 because the density of hot air is greater than that of cold air. When the transferred heat causes the temperature of middle alloy skeleton 23 to exceed its own memory temperature, middle alloy skeleton 23 deforms to bend upward. On the other hand, after the heating of the lower layer by the heating 22 is stopped, the middle alloy skeleton 23 gradually cools. When the temperature of middle alloy skeleton 23 decreases below the memory temperature, middle alloy skeleton 23 returns to the original configuration.
The top layer of elastic cut paper 24 is an elastic sheet or plate that is capable of elastic deformation. The top layer of elastic shear paper 24 is connected with the middle layer of alloy skeleton 23 by screw connection, welding, etc. Thus, the top layer elastic scissor layer 24 can deform with the deformation of the middle alloy skeleton 23, so that a part of the top layer elastic scissor layer 24 bulges to form a wavy shape as shown in fig. 1 and 2.
Fig. 2 shows a schematic operation of the anti-icing de-icing device S as mounted to the airfoil component 21. Fig. 2 (a) shows the anti-icing and deicing device S in a non-operating state. As shown in the figure, in the non-operating state, the middle alloy skeleton 23 and the top layer elastic scissor layer 24 are both in the original shapes, the bottom layer heated layer 22 is not heated, and the whole anti-icing and deicing device S is closely attached to the airfoil member 21. Fig. 2 (B) shows the anti-icing and deicing device S in an operating state. As shown in the figure, in the operating state, since the bottom layer heated by the heating layer 21 is heated by the heater, the heat deforms the middle layer laminated skeleton 23, so that the top layer elastic paper-cut layer bulges to take on a wavy shape. As a result of changing from the curved shape shown in fig. 2 (a) to the wavy shape shown in fig. 2 (B), ice adhering to the top layer elastic scissor layer 24 is crushed or pulled and peeled off from the top layer elastic scissor layer 24 with an external air flow moving at a high speed. In addition, in the absence of ice formation, ice can be inhibited from adhering to and depositing on the top layer of the elastic scissor layer 24 by the above-described action.
Fig. 3 shows an anti-icing and deicing flowchart based on the anti-icing and deicing device S. As shown in fig. 3, first, it is determined whether there is an anti-icing demand or a deicing demand. Specifically, whether or not there is ice formation and the degree of ice formation may be determined by the temperature and humidity detected by the temperature sensor and the humidity sensor that are arranged in advance in the airfoil member 21, but not limited thereto, any method may be employed as long as it is possible to determine whether or not there is ice formation and the degree of ice formation. When it is determined that there is no anti-icing demand or deicing demand, the determination is continued after a predetermined time interval. When it is determined that there is an anti-icing demand or a deicing demand, the underlayer heated layer 22 is heated at least twice by a heater, and each heating is performed at a predetermined time interval. That is, the underlying heated layer 22 is repeatedly heated and cooled at least twice. By repeatedly heating and cooling the bottom heated layer 22, the middle alloy skeleton 23 repeatedly bends upward and returns to the original shape, so that the top elastic paper-cut structure layer 24 repeatedly deforms into a wave shape and returns to the original shape. In this way, the deposition of the ice layer on the surface of the airfoil member 21 can be suppressed, while also enabling the deposited ice layer to be rapidly peeled off from the surface of the airfoil member 21.
While only selected embodiments have been chosen to illustrate the present invention, it will be apparent to those skilled in the art from this disclosure that various changes and modifications can be made herein without departing from the scope of the invention as defined in the appended claims. For example, unless specifically stated otherwise, the size, shape, position or orientation of the various components may be changed as needed and/or desired, provided that such changes do not substantially affect their intended function. Unless specifically stated otherwise, components shown directly connected or contacting each other may have intermediate structures disposed therebetween, so long as such changes do not materially affect the intended function thereof. The functions of one element may be performed by two, and vice versa, unless otherwise specified. The structure and function of one embodiment may be adopted in another embodiment or modification. All advantages need not be present in a particular embodiment at the same time. Thus, the foregoing description of embodiments according to the invention is provided for illustration only.
Claims (4)
1. An aircraft anti-icing and deicing device for anti-icing and deicing of aircraft components of an aircraft, comprising:
a bottom heated layer secured to the flight element;
a middle alloy skeleton provided on the upper portion of the bottom layer heated layer and made of a shape memory alloy, and capable of deforming or recovering deformation according to the temperature of the bottom layer heated layer; and
the top layer elastic paper-cut layer is arranged on the upper portion of the middle layer alloy skeleton and is connected with the middle layer alloy skeleton in a mode of being capable of being elastically deformed along with deformation of the middle layer alloy skeleton.
2. An aircraft anti-icing de-icing assembly as claimed in claim 1,
the heating device also comprises a heater, wherein the heater heats the bottom heated layer.
3. An aircraft anti-icing de-icing assembly as claimed in claim 2,
the heater is a silver nanowire heater.
4. An aircraft anti-icing and deicing method using an aircraft anti-icing and deicing device according to any one of claims 1 to 3, characterized in that it comprises:
determining whether there is an anti-icing demand or a de-icing demand; and
and in the case that the ice prevention requirement or the ice removal requirement is judged to exist, repeatedly heating and cooling the bottom heated layer for more than two times, so that the temperature of the middle laminated skeleton repeatedly changes between a temperature less than the memory temperature and a temperature greater than the memory temperature.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310159039.7A CN116374176A (en) | 2023-02-23 | 2023-02-23 | Anti-icing and deicing device and anti-icing and deicing method for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310159039.7A CN116374176A (en) | 2023-02-23 | 2023-02-23 | Anti-icing and deicing device and anti-icing and deicing method for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116374176A true CN116374176A (en) | 2023-07-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310159039.7A Pending CN116374176A (en) | 2023-02-23 | 2023-02-23 | Anti-icing and deicing device and anti-icing and deicing method for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116374176A (en) |
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2023
- 2023-02-23 CN CN202310159039.7A patent/CN116374176A/en active Pending
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