CN114455082A - Deicing structure based on shape memory effect and aircraft - Google Patents
Deicing structure based on shape memory effect and aircraft Download PDFInfo
- Publication number
- CN114455082A CN114455082A CN202210022202.0A CN202210022202A CN114455082A CN 114455082 A CN114455082 A CN 114455082A CN 202210022202 A CN202210022202 A CN 202210022202A CN 114455082 A CN114455082 A CN 114455082A
- Authority
- CN
- China
- Prior art keywords
- layer
- memory
- memory layer
- heating
- deicing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000003446 memory effect Effects 0.000 title claims abstract description 20
- 238000010438 heat treatment Methods 0.000 claims abstract description 56
- 230000009471 action Effects 0.000 claims abstract description 13
- 230000000694 effects Effects 0.000 claims description 12
- 238000001514 detection method Methods 0.000 claims description 10
- 229920000431 shape-memory polymer Polymers 0.000 claims description 3
- 230000004913 activation Effects 0.000 claims 1
- 230000009849 deactivation Effects 0.000 claims 1
- 229910052755 nonmetal Inorganic materials 0.000 abstract description 4
- 239000010410 layer Substances 0.000 description 251
- 238000009413 insulation Methods 0.000 description 13
- 239000000463 material Substances 0.000 description 9
- 238000005485 electric heating Methods 0.000 description 8
- 239000007769 metal material Substances 0.000 description 8
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 6
- 239000003822 epoxy resin Substances 0.000 description 6
- 229910021389 graphene Inorganic materials 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- 229920000647 polyepoxide Polymers 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 239000002131 composite material Substances 0.000 description 4
- 229920000642 polymer Polymers 0.000 description 4
- 239000000853 adhesive Substances 0.000 description 3
- 230000001070 adhesive effect Effects 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000009529 body temperature measurement Methods 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 230000009477 glass transition Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Images
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention provides a deicing structure based on a shape memory effect and an aircraft, and relates to the field of aircraft, and the deicing structure comprises a memory layer, a heating layer and a supporting layer which are sequentially arranged, wherein one side of the supporting layer, which faces the memory layer, is a corrugated surface, wave crests of the corrugated surface are abutted against and support the memory layer, and the heating layer is positioned between the memory layer and wave troughs of the corrugated surface, so that the memory layer is sunken towards the wave troughs of the corrugated surface under the action of the heating layer; the aircraft is characterized in that a multi-layer stacked structure is arranged for solving the problem that the deicing of the surface of the existing non-metal aircraft is difficult and the efficiency is low, a support layer provides stable support for an outermost memory layer, the strength requirement is met, the memory layer can deform under the action of a heating layer to form local depression, and the ice layer is separated from the surface of the memory layer by combining heat released by the heating layer, so that the ice layer attached to the surface of the memory layer is removed.
Description
Technical Field
The invention relates to the field of aircrafts, in particular to a deicing structure based on a shape memory effect and an aircraft.
Background
After the surface of the aircraft is adhered to ice, the surface morphology of the aircraft can be changed, and the fluid structure of the aircraft is influenced. In addition, for some aircrafts with special requirements, such as stealth performance and the like, special selection of the surface material of the aircraft is needed, and the single application of the special surface material cannot simultaneously meet the performance requirement and deicing requirement of the aircraft.
At present, a widely applied deicing mode is electrothermal deicing, and an electric heating metal material is used for heating the surface of an aircraft to melt the adhesion position of an ice layer, so that the ice layer is separated from the surface of the aircraft to achieve the aim of deicing. However, electrothermal deicing depends on the surface of an aircraft made of a metal material, and the metal material cannot meet special requirements such as stealth performance of the aircraft sometimes, so that when the aircraft made of a non-metal surface material is used for surface deicing, the aircraft needs to be gradually heated and melted from the outside of an ice layer, the deicing effect is poor, and for a thick area of the ice layer, the ice layer can be separated from the surface of the aircraft only by continuously heating for a long time, so that the time consumption is long, the energy consumption is high, and the requirement for quick and thorough deicing of the surface of the aircraft is difficult to meet.
Disclosure of Invention
The invention aims to provide a deicing structure based on shape memory effect and an aircraft aiming at the defects in the prior art, a multilayer overlapping structure is arranged, a support layer provides stable support for an outermost memory layer and meets the strength requirement, the memory layer can deform under the action of a heating layer to form local depressions, and the ice layer is separated from the surface of the memory layer by combining with heat released by the heating layer to remove the ice layer attached to the surface of the memory layer.
The invention aims at providing a deicing structure based on shape memory effect, which adopts the following scheme:
including memory layer, zone of heating and the supporting layer that arranges in proper order, one side that the supporting layer moves towards the memory layer is the ripple face, and the crest department butt of ripple face supports the memory layer, and the zone of heating is located between the trough of memory layer and ripple face to make the memory layer sunken towards the trough of ripple face under the zone of heating effect.
Further, the memory layer is a shape memory polymer plate and is deformed into a corrugated plate under the action of the heating layer.
Further, the corrugated surface is in a corrugated shape with convex parts and concave parts alternately distributed in sequence, and at least one convex part abuts against and supports the memory layer.
Further, the heating layer is disposed in the at least one recess and arranged along an extending direction of the recess to simultaneously heat the memory layer and the support layer.
Furthermore, heat conducting sheets which are arranged in an oriented mode are arranged in the memory layer and the supporting layer, and the heat conducting sheets are combined with the heating layer to form a heat conducting path.
Furthermore, a heat insulation layer is arranged on one side, away from the memory layer, of the supporting layer, and the heat insulation layer is connected with the memory layer.
Further, detection component is installed to the memory layer, and detection component is including being used for surveying the thickness sensor who gets the memory layer and adhering to the ice sheet and being used for surveying the temperature sensor who gets memory layer temperature.
Furthermore, the detection assembly and the heating layer are both connected with a controller, and the controller is used for controlling the starting and stopping of the heating layer.
Further, the supporting layer is a polymer plate, and gaps are reserved between the depressions formed after the memory layer is deformed and the wave troughs of the corrugated surface.
A second object of the invention is to provide an aircraft comprising a deicing structure based on shape memory effect as described above.
Compared with the prior art, the invention has the advantages and positive effects that:
(1) the problem that deicing is difficult on the surface of the existing non-metallic material aircraft and efficiency is low is solved by arranging a multi-layer stacked structure, a supporting layer provides stable support for an outermost memory layer, the strength requirement is met, the memory layer can deform under the action of a heating layer to form local depression, and the ice layer is separated from the surface of the memory layer by combining heat released by the heating layer, so that the ice layer attached to the surface of the memory layer is removed.
(2) The ice sheet is attached to the memory layer of outmost structure, the memory layer is thermotropic type memory polymer, when the memory layer is heated and is produced deformation, produce the sunken of corresponding zone of heating trough position in a plurality of positions, thereby make memory layer formation buckled plate, sunken position breaks away from with attached ice sheet, reduce the attached area of memory layer and ice sheet, the memory layer rises at zone of heating effect temperature down, heat the ice sheet that contacts the memory layer and melt, further reduce the adhesive force on ice sheet, reach the effect of deicing in coordination.
(3) When the memory layer is heated and deformed, the plurality of positions form depressions, and the memory layer is slightly displaced relative to the supporting layer, so that the memory layer relatively moves relative to the ice layer along the attachment surface position to disconnect the attachment positions of the ice layer and the memory layer surface, the attachment area of the ice layer and the memory layer surface is further reduced, and the deicing efficiency is improved.
(4) The heat that utilizes the zone of heating to provide realizes the heat altered shape and the heat transfer of memory layer, realizes mechanical action and the heat effect deicing in coordination among the deicing process, compares in from outside successive layer deicing process, can direct action and ice layer adhesion position, improves deicing efficiency to, compare in single electric heat deicing, the deicing in coordination can further improve deicing efficiency.
(5) The detection assembly is adopted to detect the temperature of the memory layer and the adhesion condition of the surface ice layer, the icing adhesion state and the deicing effect can be accurately mastered, the deformation of the memory layer can be controlled by adjusting the heating layer according to the temperature measurement, and the controllability of the deicing process is improved.
(6) The memory layer is provided with a plurality of memory layers, the memory layers are arranged on the supporting layer, the memory layers are arranged on the memory layers in a directional mode, the memory layers are arranged on the supporting layer in a directional mode, the heat conducting fins are made of materials with high heat conductivity, the transmission efficiency of heat is improved through the directional arrangement, the heat can quickly cover the icing area of the memory layers, heat loss is reduced, and energy consumption is reduced.
(7) The memory layer is corresponding to the sunken of supporting layer trough position, can make memory layer part region warp to the direction towards the supporting layer, makes this part region break away from with the ice sheet, compares in outside protrusion top and pushes away the ice sheet, can avoid because of the unable circumstances that pushes away the ice sheet of the deformation force that the adhesive force is great leads to, improves the efficiency that memory layer part breaks away from the ice sheet, avoids the memory layer to warp and is restrained and can't with the circumstances that the ice sheet breaks away from.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.
FIG. 1 is a schematic view showing the positions of a memory layer and a support layer in embodiment 1 or 2 of the present invention;
FIG. 2 is a schematic view of a shape memory based deicing structure according to embodiment 1 or 2 of the present invention;
FIG. 3 is a schematic view showing the arrangement of the heat conductive sheet in embodiment 1 or 2 of the present invention;
FIG. 4 is a schematic view of an ice layer adhered to the surface of the memory layer in embodiment 1 or 2 of the present invention;
FIG. 5 is a schematic view showing an ice layer adhered to the memory layer after deformation in embodiment 1 or 2 of the present invention;
fig. 6 is a partially enlarged schematic view of a portion a of fig. 3.
In the figure, 1, a memory layer; 2. a support layer; 3. a cavity; 4. an electrically heated strip driver; 5. a thermal insulation layer; 6. a functional portion; 7. pasting the face; 8. a heat conductive sheet; 9. a heat conducting path; 10. an ice layer; 11. a memory layer before deformation; 12. and (5) a deformed memory layer.
Detailed Description
Example 1
In an exemplary embodiment of the present invention, a shape memory based de-icing arrangement is shown in fig. 1-6.
The deicing structure based on the shape memory effect shown in fig. 1 is used for surfaces of the easily-attached ice layer 10, such as surfaces of aircrafts and vehicles, which are made of non-metallic materials, and the deicing structure based on the shape memory effect can be applied to the surfaces of the easily-attached ice layer 10 to serve as a protective layer, or the surface structure of the attached ice layer 10 can be directly replaced, and is selected according to actual requirements. In the present embodiment, the mounting on the outer surface of the wing skin of an aircraft is described as an example, the outer surface of the wing skin forms an application surface 7, and a deicing structure based on a shape memory effect is mounted on this application surface 7 without affecting the use of the functional part 6 inside the wing.
As shown in fig. 1 and 2, the deicing structure based on the shape memory effect mainly comprises a memory layer 1, a support layer 2, a heating layer and a thermal insulation layer 5 which are sequentially arranged, wherein the memory layer 1 is made of a shape memory polymer sheet material, and the support layer 2, the heating layer and the thermal insulation layer 5 are made of materials which do not influence the use of a functional part 6 at the installation position.
For example, in this embodiment, for an airfoil with stealth performance, the memory layer 1 may be made of a shape memory epoxy resin/graphene composite material that has shape memory characteristics and is beneficial to absorbing waves and transmitting waves of the airfoil; the supporting layer 2 can be made of epoxy resin/graphene composite materials, can support the memory layer 1, is beneficial to wave absorption and wave transmission, and can also play a role in heat transfer; the heating layer can provide heat required by deicing and heat and drive the memory layer 1 to complete deformation; the heat insulation layer 5 is arranged between the wing skin and the supporting layer 2, so that the loss of heat to the wing skin is reduced, and the heat utilization efficiency is improved.
By adopting the materials, the wave absorbing and wave transmitting effects of the original wing can be ensured, and it can be understood that in other embodiments, materials of the memory layer 1, the supporting layer 2, the heating layer and the thermal insulation layer 5 of other types can be selected according to different functional requirements of the aircraft, so that the work of the functional part 6 of the aircraft is not influenced by the deicing structure based on the shape memory effect, and after the deicing structure is installed, the functional part 6 can still realize the normal operation.
As shown in fig. 2, the side of the supporting layer 2 facing the memory layer 1 is a corrugated surface, the corrugated surface is a corrugated shape in which concave portions and convex portions are alternately distributed in sequence, the top ends of the convex portions are wave crests, the bottom ends of the concave portions are wave troughs, and the wave crests and the wave troughs are alternately distributed in sequence along the distribution direction of the supporting layer 2.
Meanwhile, the wave crests of the corrugated surface are abutted and supported to the memory layer 1, the memory layer 1 is located on the outermost side, the ice layer 10 is attached to the memory layer 1, the external environment directly acts on the memory layer 1, in order to guarantee the stability of the memory layer 1, the convex parts on the supporting layer 2 can support the memory layer 1, and the wave crests are located on the memory layer 1 to form abutting.
It can be understood that the wave crests of the supporting layer 2 are in an abutting supporting relationship rather than a fixed connection relationship between the memory layers 1, so that the requirement of the memory layers 1 on small displacement generated when the memory layers are deformed due to memory characteristics can be met; specifically, when the memory layer 1 is deformed by heating, the memory layer 1 slightly displaces relative to the support layer 2, and under the action, the memory layer 1 relatively moves relative to the ice layer 10 along the attachment surface position, so that the attachment position between the ice layer 10 and the surface of the memory layer 1 is disconnected, the attachment area between the ice layer 10 and the surface of the memory layer 1 is further reduced, and the deicing efficiency is improved.
In addition, the micro displacement does not affect the stable supporting relationship between the memory layer 1 and the supporting layer 2, and the memory layer 1 can still maintain good strength to meet the requirement before deforming; similarly, a certain amount of reserve can be provided for the length or width of the memory layer 1, so that a small gap is left between part of the wave crest and the memory layer 1, and the requirement of the deformation amount is met. It can be understood that, for some situations of realizing deformation by depending on the material property of the memory layer 1, the memory layer 1 does not generate relative displacement with the support layer 2 when deformed, and then a part of wave crests can be connected with the memory layer 1, so that the relative position of the wave crests is ensured, and the requirement of the whole body on strength is met.
As shown in fig. 2, in order to stabilize the position of the memory layer 1, at least one convex portion abuts and supports the memory layer 1, the heating layer is positioned between the memory layer 1 and the wave trough of the corrugated surface, and can communicate with and heat the memory layer 1 and the supporting layer 2 simultaneously, and the memory layer 1 can generate the wave trough depression facing the corrugated surface when being heated.
As shown in fig. 4 and 5, the ice layer 10 is attached to the memory layer 11 in the deformation region of the outermost layer structure, the memory layer 1 is made of a thermotropic memory polymer, and when the memory layer 1 is deformed by heating, depressions corresponding to the wave trough positions of the heating layer are generated at a plurality of positions, so that the deformed memory layer 12 forms corrugated plates, and the depressions are separated from the attached ice layer 10, thereby reducing the attachment area between the deformed memory layer 12 and the ice layer 10.
As shown in fig. 3, the temperature of the memory layer 1 rises under the action of the heating layer, and the ice layer 10 contacting the memory layer 1 is heated and melted, so that the adhesion of the ice layer 10 is further reduced, and the deicing effect is cooperatively achieved.
In combination with the heating layer, the memory layer 1 used in this embodiment is a shape memory epoxy resin/graphene composite material, and is located on the outermost side in actual use, and is elastically deformed when heated to a required temperature of 60 ℃. It should be noted that the shape of the memory layer 1 is divided into two types, namely before deformation and after deformation, and the shape before deformation is the shape adapted to the installation position, such as the wing profile of an aircraft wing in the embodiment; after the deformation, the steel sheet is not deformed in the chord direction, but is corrugated in the rib direction, and the shape thereof is due to pre-deformation during the machining.
The heat that utilizes the zone of heating to provide realizes the heat altered shape and the heat transfer of memory layer 1, realizes mechanical action and the thermal action deicing in coordination among the deicing process, compares in from outside successive layer deicing process, can direct action and ice layer 10 attached position, improves deicing efficiency to, compare in single electric heat deicing, the deicing efficiency can further be improved in coordination.
Referring to fig. 3 and 6, the support layer 2 is a polymer plate, and the memory layer 1 is deformed to form recesses and gaps are reserved between the valleys of the corrugated surface. In the embodiment, the support layer 2 is made of an epoxy resin/graphene composite material, supports the memory layer 1 and transfers heat, and the corrugated surface facing the memory layer 1 is maintained and has no deformation before and after heating; meanwhile, after the memory layer 1 is heated by the heating layer and the memory layer 1 deforms, the memory layer 1 forms a corrugated plate-shaped structure, the corrugated surfaces of the corrugated plate-shaped memory layer 1 and the supporting layer 2 tend to be attached, gaps are still left and cannot be completely attached, and the installation cavity 3 of the heating layer is reserved.
In order to ensure the heating effect of the heating layer, the heating layer is arranged in at least one concave part and is arranged along the extending direction of the concave part so as to heat the memory layer 1 and the support layer 2 simultaneously; as shown in fig. 3 and 6, the heating layer penetrates the entire deicing position along the chord direction, and heats the memory layer 1 and the support layer 2 and drives the memory layer 1 to deform. The heating layer is arranged at a position far away from the front edge of the wing so as to ensure the wave-transmitting and wave-absorbing functions of the non-metal material.
The memory layer 1 and the support layer 2 are both internally provided with heat conducting fins 8 which are arranged in an oriented way, and the heat conducting fins 8 are combined with the heating layer to form a heat conducting passage 9; the heat conducting sheet 8 in the present embodiment is made of graphene, and a heat conducting path 9 along the chord direction is formed inside the memory layer 1 made of shape memory epoxy resin; at the same time, heat conducting paths 9 are formed inside the support layer 2 of epoxy resin in the chord direction.
The heating layer may optionally be provided with an electric heating strip actuator 4, the electric heating strip actuator 4 being capable of releasing heat while heating the memory layer 1 and the support layer 2.
As shown in fig. 1 and fig. 2, a detection assembly is used for detecting the temperature of the memory layer 1 and the adhesion condition of the ice layer 10 on the surface, the detection assembly is mounted on the memory layer 1, and the detection assembly comprises a thickness sensor for measuring the adhesion condition of the ice layer 10 on the memory layer 1 and a temperature sensor for measuring the temperature of the memory layer 1; the detection component and the heating layer are both connected with a controller, and the controller is used for controlling the starting and stopping of the heating layer; the icing adhesion state and the deicing effect can be accurately mastered, the deformation of the memory layer 1 can be controlled by adjusting the heating layer according to temperature measurement, and the controllability of the deicing process is improved.
In this embodiment, the ice thickness sensor may be an existing thickness sensor, such as a non-contact ultrasonic sensor, and the thickness of the adhered ice layer 10 may be measured without affecting the operation of the functional portion 6. The ice thickness sensor and the temperature sensor are arranged in an area which is easy to accumulate ice and outside the memory layer 1 and are uniformly distributed along the chord direction.
The thermal insulation layer 5 in this embodiment is disposed between the wing skin and the support layer 2, and is closely attached to the surface of the wing skin along the chord direction.
Example 2
In another exemplary embodiment of the present invention, as shown in fig. 1-6, an aircraft is provided that utilizes a shape memory based de-icing arrangement as in embodiment 1.
The deicing structure based on the shape memory effect is installed on the wing of the aircraft as in embodiment 1, the corresponding thermal insulation layer 5 is installed on the application surface 7 of the wing, and the normal operation of the functional part 6 in the wing is not influenced by the deicing structure based on the shape memory effect.
When the ice accretion happens, the ice thickness sensor and the temperature sensor which are arranged on the memory layer 1 send signals to the controller, the controller sends an opening signal to the electric heating strip driver 4, the electric heating strip driver 4 releases heat, the memory layer 1 and the supporting layer 2 are heated simultaneously, the heat released by the electric heating strip driver 4 is transmitted along the icing direction in a single direction due to the heat insulation effect of the heat insulation layer 5, and the temperature of one side, far away from the wing, of the heat insulation layer 5 is rapidly increased. When 60 ℃ is reached, the memory layer 1 deforms according to the predetermined shape until the ice accretion is removed. The memory layer 1, the support layer 2 and the heat insulation layer 5 are all made of non-metal materials, and interference of metal materials is avoided in the electromagnetic wave emitting direction.
When the electric heating strip driver 4 starts to heat, the heat conduction path 9 is formed along the chord direction of the graphene orientation arrangement, so that the temperature of the memory layer 1 and the support layer 2 is rapidly increased.
As shown in fig. 1 and 4, before the memory layer 1 deforms, the shape of the memory layer is the same as that of a common wing, when the electric heating strip driver 4 starts to release heat, the memory layer 1 rapidly rises to reach the glass transition temperature of 60 ℃, a part of specific surface is inwards sunken due to the shape memory effect, and the surface of the ice layer 10 is separated from the outer surface of the wing.
Through the sunken of memory layer 1 corresponding supporting layer 2 trough position, can make memory layer 1 subregion warp to the direction towards supporting layer 2, make this subregion break away from with ice sheet 10, compare in outside protrusion top push away ice sheet 10, can avoid can't push away the condition of ice sheet 10 because of the deformation power that the adhesive force is great leads to, improve the efficiency that memory layer 1 part breaks away from ice sheet 10, avoid memory layer 1 to warp and restrict the condition that can't break away from with ice sheet 10.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. Deicing structure based on shape memory effect, its characterized in that is including the memory layer, zone of heating and the supporting layer that arrange in proper order, and one side of supporting layer orientation memory layer is the ripple face, and the crest department butt of ripple face supports the memory layer, and the zone of heating is located between the trough of memory layer and ripple face to make the memory layer sunken towards the trough of ripple face under the zone of heating effect.
2. Deicing structure based on the shape memory effect as claimed in claim 1, characterized in that said memory layer is a sheet of shape memory polymer, deformed into a corrugated sheet by the action of the heating layer.
3. Deicing structure as claimed in claim 1, characterized in that said undulated surface is undulated with alternating succession of projections and recesses, at least one projection abutting and supporting a memory layer.
4. Deicing structure as claimed in claim 3, characterized in that said heating layer is provided in at least one recess and is arranged along the extension of the recess so as to heat both the memory layer and the supporting layer.
5. The deicing structure based on shape memory effect as claimed in claim 1, wherein the memory layer and the support layer are provided with directionally arranged heat conducting sheets, and the heat conducting sheets form a heat conducting path in combination with the heating layer.
6. Deicing structure based on shape memory effect as claimed in claim 1, characterized in that the side of the supporting layer remote from the memory layer is provided with a heat-insulating layer, which is connected to the memory layer.
7. Shape memory based deicing structure according to claim 1, characterized in that said memory layer is fitted with a detection assembly comprising a thickness sensor for detecting the adhesion of the memory layer to the ice layer and a temperature sensor for detecting the temperature of the memory layer.
8. The shape memory based deicing structure of claim 7 wherein said detection assembly and said heating layer are each connected to a controller, said controller configured to control the activation and deactivation of said heating layer.
9. Deicing structure based on the shape memory effect as claimed in claim 1, characterized in that said supporting layer is a polymeric sheet, the memory layer being deformed so as to form recesses leaving gaps between the valleys of the undulated surface.
10. An aircraft, characterized in that it comprises a deicing structure based on shape memory according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210022202.0A CN114455082A (en) | 2022-01-10 | 2022-01-10 | Deicing structure based on shape memory effect and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210022202.0A CN114455082A (en) | 2022-01-10 | 2022-01-10 | Deicing structure based on shape memory effect and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114455082A true CN114455082A (en) | 2022-05-10 |
Family
ID=81409602
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210022202.0A Pending CN114455082A (en) | 2022-01-10 | 2022-01-10 | Deicing structure based on shape memory effect and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114455082A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115649454A (en) * | 2022-09-23 | 2023-01-31 | 陕西飞机工业有限责任公司 | Hot air anti-icing structure for front edge of wing |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2457502A1 (en) * | 1974-12-05 | 1976-06-10 | Eichenauer Fa Fritz | Aircraft anti-icing device - has outer shell over heat conducting sheet with electric heating elements |
| US5558304A (en) * | 1994-03-14 | 1996-09-24 | The B. F. Goodrich Company | Deicer assembly utilizing shaped memory metals |
| US5686003A (en) * | 1994-06-06 | 1997-11-11 | Innovative Dynamics, Inc. | Shape memory alloy de-icing technology |
| US20090283605A1 (en) * | 2006-07-24 | 2009-11-19 | Microheat Inc. | Vehicle surfaces cleaning and de-icing system and method |
| CN204368433U (en) * | 2014-12-23 | 2015-06-03 | 中国民航大学 | A kind of wing deicing device driven based on SMA |
| CN110498050A (en) * | 2019-08-24 | 2019-11-26 | 昆明研顶技术开发有限公司 | A method of aircraft surface deicing is carried out using memorial alloy |
| CN111645865A (en) * | 2020-07-07 | 2020-09-11 | 江西克莱威纳米碳材料有限公司 | Deicing device for wing skin |
| CN112969639A (en) * | 2018-10-26 | 2021-06-15 | 列奥纳多股份公司 | Blade for an aircraft with hovering capability and method of deicing from the blade |
-
2022
- 2022-01-10 CN CN202210022202.0A patent/CN114455082A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2457502A1 (en) * | 1974-12-05 | 1976-06-10 | Eichenauer Fa Fritz | Aircraft anti-icing device - has outer shell over heat conducting sheet with electric heating elements |
| US5558304A (en) * | 1994-03-14 | 1996-09-24 | The B. F. Goodrich Company | Deicer assembly utilizing shaped memory metals |
| US5686003A (en) * | 1994-06-06 | 1997-11-11 | Innovative Dynamics, Inc. | Shape memory alloy de-icing technology |
| US20090283605A1 (en) * | 2006-07-24 | 2009-11-19 | Microheat Inc. | Vehicle surfaces cleaning and de-icing system and method |
| CN204368433U (en) * | 2014-12-23 | 2015-06-03 | 中国民航大学 | A kind of wing deicing device driven based on SMA |
| CN112969639A (en) * | 2018-10-26 | 2021-06-15 | 列奥纳多股份公司 | Blade for an aircraft with hovering capability and method of deicing from the blade |
| CN110498050A (en) * | 2019-08-24 | 2019-11-26 | 昆明研顶技术开发有限公司 | A method of aircraft surface deicing is carried out using memorial alloy |
| CN111645865A (en) * | 2020-07-07 | 2020-09-11 | 江西克莱威纳米碳材料有限公司 | Deicing device for wing skin |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115649454A (en) * | 2022-09-23 | 2023-01-31 | 陕西飞机工业有限责任公司 | Hot air anti-icing structure for front edge of wing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20150023792A1 (en) | Wind turbine rotor blade de-icing process and wind turbine rotor blade de-icing system | |
| CN114455082A (en) | Deicing structure based on shape memory effect and aircraft | |
| US5351918A (en) | Electrical heater de-icer | |
| BR9917428A (en) | Airplane defrost system and method by zone | |
| EP2390182B1 (en) | Aircraft heating system | |
| JP2021151865A (en) | Composite aerostructure with integrated heating element | |
| CA2615166A1 (en) | Energy-efficient electro-thermal ice-protection system | |
| US11296368B2 (en) | Rechargeable battery comprising a cooling device | |
| CN110510102B (en) | Attachable self-resistance heating/super-hydrophobic integrated gradient film material | |
| CN109131821B (en) | Slidable connecting structure | |
| CN113148183A (en) | Plasma hot knife and hydrophobic material combined type deicing device and application | |
| JP7047720B2 (en) | Solar cell module with snow melting function | |
| CN111731485B (en) | Autonomous intermittent deicing device and installation method and deicing method thereof | |
| JPH04103497A (en) | De-icing device | |
| CN211531351U (en) | Ice melting device for tunnel of electrified railway | |
| CN220325846U (en) | Energy-saving directional heating plate | |
| EP3639622B1 (en) | Flexible resistor | |
| CN115610641A (en) | Wing | |
| CN114435597A (en) | Temperature difference power generation device for wing anti-icing and deicing assembly, anti-icing and deicing assembly and method | |
| CN201820746U (en) | Soft ceramic composite metal substrate | |
| CN215442448U (en) | Anti-aging multi-layer composite waterproof coiled material | |
| CN113562199B (en) | Heating structure suitable for spacecraft low thrust engine | |
| CN221972711U (en) | Heat preservation composite board with energy storage function | |
| WO2001008463A3 (en) | Aircraft de-icing system | |
| CN218745685U (en) | Semiconductor bonding wire hot pressing plate capable of being rapidly heated |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20220510 |