CN117284470A - Electric heating ice machine preventing and removing wing skin structure and forming method thereof - Google Patents
Electric heating ice machine preventing and removing wing skin structure and forming method thereof Download PDFInfo
- Publication number
- CN117284470A CN117284470A CN202210695465.8A CN202210695465A CN117284470A CN 117284470 A CN117284470 A CN 117284470A CN 202210695465 A CN202210695465 A CN 202210695465A CN 117284470 A CN117284470 A CN 117284470A
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- skin
- heating wire
- wing
- front edge
- icing
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- 238000005485 electric heating Methods 0.000 title claims abstract description 47
- 238000000034 method Methods 0.000 title claims abstract description 24
- 238000010438 heat treatment Methods 0.000 claims abstract description 133
- 239000000835 fiber Substances 0.000 claims description 20
- 239000004744 fabric Substances 0.000 claims description 13
- 239000003292 glue Substances 0.000 claims description 11
- 238000001514 detection method Methods 0.000 claims description 6
- 238000000465 moulding Methods 0.000 claims description 5
- 238000000638 solvent extraction Methods 0.000 claims description 5
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
- 238000004140 cleaning Methods 0.000 claims description 3
- 239000011889 copper foil Substances 0.000 claims description 2
- 238000005422 blasting Methods 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 4
- 238000012546 transfer Methods 0.000 abstract description 2
- 239000010410 layer Substances 0.000 description 64
- 230000008569 process Effects 0.000 description 9
- 238000005265 energy consumption Methods 0.000 description 8
- 239000002313 adhesive film Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 230000002265 prevention Effects 0.000 description 4
- 238000005488 sandblasting Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 239000012790 adhesive layer Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000014509 gene expression Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
-
- 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)
- Mechanical Engineering (AREA)
- Road Paving Structures (AREA)
Abstract
The invention provides an electric heating deicing machine wing skin structure and a forming method thereof, wherein the wing skin structure comprises a front edge skin and a heating element which is arranged in the front edge skin and is integrally formed with the front edge skin; the heating element comprises an electric heating wire film and an electrode patch, wherein the electric heating wire film is of a thin layer structure and sequentially comprises an insulating layer, an electric heating wire layer and an insulating layer, and at least one side of the electric heating wire layer is provided with a heat conducting layer; the inner end surface of the electrode patch is connected with the heating wire film, and the outer end surface penetrates out of the inner surface of the front edge skin and is connected with the power supply cable; the leading edge skin is mounted to the leading edge of the wing. According to the invention, the heating element and the wing skin are integrally formed, the heating element is close to the outer surface of the wing skin, so that heat transfer is facilitated, secondary arrangement, installation and operation are reduced, the heat conduction mode and the electric connection mode of the heating element are optimized, the structural form is simple, and the deicing efficiency and the structural reliability are improved.
Description
Technical Field
The invention relates to the technical field of wing deicing, in particular to an electric heating deicing machine wing skin structure and a forming method thereof.
Background
In the high-altitude flight process of the aircraft, due to low high-altitude temperature and supercooled water drops in the cloud, the wing front edge is frozen, the air flow is seriously affected by the wing front edge, and when the wing front edge is frozen seriously, the upper and lower pressure difference on the surface of the wing is changed, so that the flight performance is affected. It is therefore desirable to design an aircraft wing deicing system that deice areas of ice.
The main deicing methods at present are mechanical deicing, electrothermal deicing, hot gas deicing and the like. The mechanical deicing structure is complex, and the aerodynamic profile of the wing is greatly influenced. The hot gas deicing also has the problems of complex structure and the like, the pipeline connection can increase the structural weight, and the deicing efficiency is low. The traditional electrothermal deicing method is mainly to paste heating elements on the inner surface of the wing skin, and heat the skin for deicing by the heating elements, so that the heating element arrangement method has the problems of low heating efficiency, low heat conduction, huge energy consumption and the like, and the heating elements are troublesome to arrange on the inner surface of the skin.
Therefore, there is a need for an ice control structure that has high deicing efficiency, low energy consumption, and easy arrangement.
Disclosure of Invention
Aiming at the technical problems of low deicing efficiency, high energy consumption, complex arrangement of heating elements and the like of wings in the prior art, the invention provides an electric heating deicing prevention and removal machine wing skin structure and a forming method thereof.
The invention solves the problems as follows:
the invention provides an electric heating deicing machine wing skin structure, which comprises a front edge skin and heating elements, wherein the heating elements are arranged in the front edge skin and are integrally formed with the front edge skin; the heating element comprises an electric heating wire film and an electrode patch; the heating wire film is of a thin layer structure and sequentially comprises an insulating layer, a heating wire layer and an insulating layer, wherein at least one side of the heating wire layer is provided with a heat conducting layer; the inner end surface of the electrode patch is connected with the electric heating wire film, and the outer end surface of the electrode patch penetrates out of the inner surface of the front edge skin and is connected with the power supply cable.
Further, the electrode patch is of a multi-layer step structure, the area of the inner end surface connected with the electric heating wire film is large, and the area of the outer end surface connected with the power supply cable is small.
Further, the electrode patch is divided into an anode and a cathode, and the anode patch and the cathode patch are respectively used for being connected with the anode and the cathode of the heating wire film.
Further, the heating element is a plurality of pieces and is arranged in the front edge skin in a partitioning manner.
Further, heat conducting layers are arranged on two sides of the heating wire layer, and the heat conducting layers are copper foils; and a glue film layer is paved on the contact surfaces of the heating wire film, the electrode patch and the front edge skin.
Further, the wing skin structure further comprises an upper skin and a lower skin, wherein the upper skin and the lower skin are fixed on the wing skeleton, and the front edge skin is fixed on the upper skin and the lower skin.
Further, a plurality of temperature sensors and icing sensors are arranged on the inner side of the joint of the front edge skin and the upper skin and the lower skin, and a control unit and a heating power supply are arranged on the inner side of the machine body;
the icing sensor is used for detecting an icing area and icing degree of the outer surface of the wing skin and transmitting the icing area and icing degree to the control unit;
the temperature sensor is used for detecting the temperature of the wing skin and transmitting the temperature to the control unit;
the control unit controls the heating element to heat the icing region according to the detection result of the icing sensor, and regulates and controls the temperature of the heating element according to the detection result of the temperature sensor;
the heating power supply is used for supplying power to the heating element and sharing power with other equipment on the machine.
Further, the icing sensor and the temperature sensor adopt an intermittent working mode; the control unit controls the heating element to preheat the skin at low temperature so that the temperature of the skin is higher than the icing point.
The invention also provides a forming method of the electric heating ice preventing and removing machine wing skin structure, which comprises the following steps:
preparing an electric heating wire film;
paving a plurality of fiber cloths and a glue film layer in a mold, and partitioning and arranging an electric heating wire film and an electrode patch on the glue film layer according to position requirements;
after the laying is completed, a glue film layer is laid on the surfaces of the heating wire film and the electrode patch, and the pretreated fiber cloth is laid on the heating wire film and the electrode patch to complete the laying;
and after the skin is laid, placing the wing front edge skin into an autoclave or a vacuum curing furnace to finish the curing and molding of the wing front edge skin.
Further, the forming method further comprises the step of carrying out surface sand blasting on the heating wire film and the electrode patch before laying; and after the front edge skin is solidified and molded, cleaning the surface of the electrode patch, and connecting a power supply cable.
The invention has the beneficial effects that:
the invention provides an electric heating ice preventing and removing wing skin structure and a forming method thereof, which have the advantages that:
(1) The heating element is arranged between the fiber cloths of the wing skin, is a heating wire film, has thin thickness, light weight and good shape following performance, and can not influence the structural performance of the skin in a normal state and a heating state.
(2) The power supply interface of the heating element adopts an electrode patch structure, the heating wire film is buried in the fiber layer, and the power supply interface is positioned on the inner surface of the skin and is directly connected with the outside. On the one hand, the problem that the power supply cable is connected with the internal heating element in the forming process is solved, the problem that the power supply cable is damaged due to improper operation in the traditional forming process is prevented, the success rate of products is improved, the operation difficulty in the forming process is simplified, and the working procedures of reserving cable through holes and the like are avoided. On the other hand, in the use process, once the power supply cable of the traditional electric heating deicing prevention structure is damaged, the power supply interface is difficult to be connected with a new cable, and the wing loses the deicing prevention function.
(3) The inner space of the front edge of the wing of the high-speed unmanned aerial vehicle is smaller, the installation and arrangement of the heating element are difficult, and the weight of the whole unmanned aerial vehicle can be increased due to the fact that the heating element is fixed by the connecting piece. The heating element and the wing skin are integrally formed, the heating element is embedded between the fiber cloth layers, the overall effect is good, the secondary fixing operation of the heating element on the inner surface of the skin is avoided, the process flow is simplified, the operation difficulty is reduced, and the reliability of the system is improved.
(4) Heating elements generally consume relatively large amounts of power and consume large amounts of energy during operation. The heating element is close to the outer surface of the skin and is close to the ice-forming area, the heat conduction path is shortened, the heat conduction is fast, and meanwhile, the heat conduction layers are arranged on the two sides of the heating wire, so that the heat conduction efficiency is improved, and the heating element has important significance in reducing energy consumption, fast deicing, ensuring flight safety and prolonging the endurance time of the whole machine. In addition, the heating elements are arranged in a partitioning mode, heating control can be performed on the heating elements in each area respectively, the whole energy consumption can be effectively reduced, and the effect of improving the endurance time of the aircraft is remarkable.
(5) The heating element can preheat the skin at low temperature, so that the temperature of the skin is higher than the icing point, and the icing problem is avoided.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is evident that the drawings in the following description are only some embodiments of the present invention and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
FIG. 1 is a schematic view of an electrically heated ice control machine wing skin structure provided in an embodiment of the present invention;
FIG. 2 is a schematic view of a heating element and leading edge skin lay-up configuration according to an embodiment of the present invention;
FIG. 3 is a schematic illustration of an arrangement of a heating element and a leading edge skin provided in accordance with an embodiment of the present invention;
fig. 4 is a control schematic diagram of an electric heating ice control machine wing skin structure according to an embodiment of the present invention.
The following reference numerals are included in the drawings:
1. a heating element; 1-1, heating wire film; 1-2, electrode patches; 2-1, leading edge skin; 2-2, upper skin; 2-3, lower skin; 3. a temperature sensor; 4. an icing sensor; 5. a control unit; 6. and a heating power supply.
Detailed Description
The technical scheme of the present invention will be described in detail by embodiments with reference to the accompanying drawings.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the present application. The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise.
The invention provides an electric heating deicing machine wing skin structure, which comprises a front edge skin and heating elements, wherein the heating elements are arranged in the front edge skin 2-1 and are integrally formed with the front edge skin; the heating element 1 comprises an electric heating wire film 1-1 and an electrode patch 1-2; the electric heating wire film is of a thin layer structure and sequentially comprises an insulating layer, an electric heating wire layer and an insulating layer, wherein at least one side of the electric heating wire layer is provided with a heat conducting layer; the inner end surface of the electrode patch is connected with the heating wire film, and the outer end surface penetrates out of the inner surface of the front edge skin and is connected with the power supply cable; the leading edge skin is mounted on the leading edge of the wing and follows the shape of the wing structure.
According to the invention, the heating element and the wing skin are integrally formed, the heating element is arranged in the wing skin and is close to the outer surface of the skin, the heat conduction layer is added to improve the heat conduction area, the ice prevention and removal efficiency is improved, the energy consumption is reduced, and the requirement of secondary installation of the heating element is simultaneously avoided; the electrode patch is adopted for electric connection, so that the reliability and maintainability are improved. The wing skin structure has excellent ice preventing and removing performance.
The technical scheme of the invention is described in detail below in connection with a specific embodiment.
As shown in fig. 1, an electrically heated deicing wing skin structure mainly comprises a composite material skin and a heating element 1, wherein the composite material skin comprises an upper skin 2-2, a lower skin 2-3 and a front edge skin 2-1. The front edge skin 2-1 is formed by laying fiber layers and adhesive film layers in multiple layers, and the heating element 1 is arranged in the front edge skin 2-1 and near the outer surface of the front edge skin. The upper and lower skins are fixed on the wing skeleton by cementing and riveting, and the front edge skin 2-1 is connected with the upper and lower skins by cementing. Inside the wing skin structure there are also arranged icing sensors 4 and temperature sensors 3. Furthermore, a control unit 5 and a heating power supply 6 are arranged inside the fuselage.
The heating element 1 is mainly used for heating the surface of the skin, and the temperature of the outer surface of the skin is higher than the temperature of an icing point so as to melt the ice layer on the surface, thereby achieving the purpose of preventing and removing ice. In the invention, the heating element and the front edge skin are integrally paved and formed, and the heating element and the skin are integrated after the skin is solidified.
As shown in fig. 2, the heating element 1 includes a heating wire film 1-1 and electrode patches 1-2.
The heating wire film 1-1 is of a thin layer structure and sequentially comprises an insulating layer, a heat conducting layer, a heating wire layer, a heat conducting layer and an insulating layer. Wherein, the electric heating wires of the electric heating wire layer are uniformly distributed between the two heat conduction layers (such as copper foil sheets) and are main heating elements; the heat conducting layers are arranged on two sides of the heating wire layer and used for increasing the heat conducting area, improving the deicing efficiency, ensuring the heat conducting uniformity and avoiding local heating, and in other embodiments, the heat conducting layers can be arranged on one side close to the outer surface of the skin; the insulating layer realizes the insulation treatment between the heating wire film 1-1 and the front edge skin.
The electrode patch 1-2 comprises positive and negative poles which are respectively connected with the positive and negative poles of the electric heating wires in the electric heating wire film; the inner end surface of the electrode patch is connected with one end of the heating wire film, the outer end surface penetrates out of the inner surface of the front edge skin and is connected with a power supply cable of a heating power supply, and the connection between the heating element in the skin and the power supply system cable of the unmanned aerial vehicle is realized. Preferably, the electrode patch adopts a multi-layer step structure, the area of the inner end surface connected with the electric heating wire film is large, the area of the outer end surface connected with the electric power supply cable is small, and as shown in fig. 2, the electrode patch adopts mechanical processing molding, and the curvature of the profile surface and the curvature of the outer surface of the wing are kept consistent. In the integral molding process of the heating element and the front edge skin, part of the fiber layer of the front edge skin is paved on part of the steps of the electrode patch, the electrode patch is pressed inside the front edge skin, the strength is increased, and the electrode patch is prevented from falling off. Preferably, the width of the single-layer step edge is not less than 5mm, so that the fiber cloth is convenient to lap.
Preferably, the heating elements are arranged in a multi-piece and partition mode, as shown in fig. 3, according to the arrangement of the icing region, the heating elements can be respectively heated and controlled, so that the ice preventing and removing efficiency is improved, the energy consumption of the whole aircraft is reduced, and the effect of improving the endurance time of the aircraft is remarkable.
The icing sensor 4 and the temperature sensor 3 are arranged in a plurality according to the monitoring requirement of the icing area or the heating element, and are arranged at the inner side of the bonding position of the front edge skin 2-1 and the upper skin and the lower skin. The icing sensor 4 is mainly used for detecting icing areas and icing degrees of the outer surface of the wing leading edge, when the icing sensor detects icing of the outer surface of the wing skin (the icing detector responds to sound waves reflected back after object transmission based on the working principle of sound wave detection, the echo amplitude of the sound waves sent by the sensor is fixed under the condition that no ice layer exists, when the surface of the wing skin is iced, echo amplitude signals change, the thickness of the icing layer is different, the amplitude signal change amount is different, and therefore whether the surface is iced or not and the thickness of the ice layer are judged), the icing sensor transmits the icing information to the control unit in the form of electric signals, and the control unit heats the icing areas through controlling the heating element to melt the ice layer. The temperature sensor is mainly used for detecting the temperature of the surface of the skin, monitoring the heating temperature of the heating element, transmitting temperature data to the control unit, and preventing the skin structure from being damaged due to overhigh temperature of a heating area.
The control unit 5 is mainly used for collecting detection data of the icing sensor 4 and the temperature sensor 3 and controlling the heating element to work. The plurality of heating elements are connected to the control unit 5 by cables, the heating elements being individually controllable. The control unit 5 can also control the heating element to preheat the skin at low temperature, so that the temperature of the skin is higher than the icing point, and the icing problem is avoided.
As shown in fig. 4, when the icing sensor 4 detects the icing area and the icing degree of the outer surface of the wing leading edge 2-1, the icing sensor 4 transmits the icing area and the icing degree to the control unit 5 in the form of electric signals, the control unit 5 controls the heating element 1 to heat the icing area, meanwhile, the temperature sensor 3 monitors the skin temperature of the heating area, the temperature is fed back to the control unit 5, and the control unit 5 regulates and controls the temperature of the heating element 1 again. When the temperature sensor 3 detects that the skin temperature reaches the set value, the control unit 5 maintains the heating element 1 at a constant temperature. And the whole regulation and control process is carried out until the ice layer in the ice formation area is completely melted, and the ice layer is taken away by the air flow. At this time, the icing sensor 4 gives the control unit 5 an icing-free signal, and the control unit 5 pauses the heating of the heating element 1. The heating power supply 6 is mainly used for supplying power to the heating element and is shared with other devices on the machine.
Preferably, in order to reduce the energy consumption, the icing and temperature sensor is operated intermittently. The control unit 5 controls whether the icing sensor is on or not according to the flying height and the atmosphere environment, and then judges the icing degree. According to the working state of the heating element, the control unit 5 controls whether the temperature sensor is started or not, and monitors the skin temperature.
According to the electric heating deicing machine wing skin structure provided by the invention, the heating element and the wing skin are integrally formed, and the heating element is close to the outer surface of the wing skin, so that heat transfer is facilitated, and secondary arrangement and installation operations are reduced. The electric heating deicing structure is simple in form, obvious in effect and high in reliability.
The invention also provides a method for integrally forming the heating element and the wing leading edge skin, which specifically comprises the following steps:
s1, preparing an electric heating wire film, and performing sand blasting on the surfaces of the electric heating wire film and the electrode patch;
the electric heating wire film is paved in the die according to the insulating layer, the heat conducting layer, the electric heating wire layer, the heat conducting layer and the insulating layer, so that two ends of the electric heating wire are ensured to stretch out, and the electric heating wire film is paved and then is put into an autoclave or a vacuum curing furnace for curing and forming. Then, sand blasting is carried out on the surfaces of the heating wire film and the electrode patch, so that the roughness of the surfaces of the film and the electrode patch is increased, and the interlayer binding force with the fiber cloth is improved.
S2, paving a plurality of layers of fiber cloth and a glue film layer in a die, and partitioning and arranging an electric heating wire film and an electrode patch on the glue film layer according to position requirements;
in order to bring the heating wire film close to the outer surface of the front edge skin, preferably, two layers of fiber cloth can be laid.
The electrode patches are crimped at the positive and negative ends of the heating wire according to the positive and negative polarities.
S3, paving a glue film layer on the surface of the heating element after paving, and paving the pretreated fiber cloth on the heating element to finish paving;
the fiber cloth is pretreated, an electrode patch outlet is reserved at the position of the fiber cloth corresponding to the electrode patch, and the number of layers of the fiber cloth is designed according to the skin strength.
S4, placing the wing front edge skin into an autoclave or a vacuum curing furnace after the skin is laid, and curing and forming the wing front edge skin;
s5, cleaning the surface of the electrode patch, and connecting a power supply cable.
The electrode patch is required to be treated by the solidified and molded front edge skin, the adhesive layer on the surface of the electrode patch is cleaned in the skin molding process, and a cable is welded on the surface of the electrode patch and used for being connected with a heating power supply of the unmanned aerial vehicle.
In the invention, the heating element and the wing front edge skin are integrally formed, the two sides of the electric heating wire film are added with the adhesive film layers, and the adhesive film layers are connected with the inner surfaces of the electrode patches, so that the strength and the stability of the integral forming can be improved by the adhesive film layers; the fiber layer is paved at the electrode patch to be of a multi-layer lap joint structure, and fiber cloth is not paved at the boss at the uppermost layer of the electrode patch, so that the connection stability of the electrode patch is improved. The heating element and the covering fiber cloth are integrally formed, the electrode patch is arranged at the power supply interface of the heating wire film and is directly connected with the outside, and the problem that the power supply interface of the heating element is difficult is solved.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
The invention is not described in detail in a manner known to those skilled in the art.
Claims (10)
1. An electric heating deicing machine wing skin structure is characterized by comprising a front edge skin and a heating element which is arranged in the front edge skin and is integrally formed with the front edge skin; the heating element comprises an electric heating wire film and an electrode patch; the heating wire film is of a thin layer structure and sequentially comprises an insulating layer, a heating wire layer and an insulating layer, wherein at least one side of the heating wire layer is provided with a heat conducting layer; the inner end surface of the electrode patch is connected with the electric heating wire film, and the outer end surface of the electrode patch penetrates out of the inner surface of the front edge skin and is connected with the power supply cable.
2. The electrically heated ice control machine wing skin structure according to claim 1, wherein the electrode patch has a multi-layered stepped structure, and an inner end surface connected to the heating wire film has a large area and an outer end surface connected to the power supply cable has a small area.
3. The electrically heated ice control machine wing skin structure according to claim 2, wherein the electrode patch is divided into a positive electrode and a negative electrode, and is respectively connected with the positive electrode and the negative electrode of the heating wire film.
4. The electrically heated icebreaker wing skin structure of claim 3, wherein the heating element is a plurality of pieces, zoned within the leading edge skin.
5. The electric heating deicing wing skin structure according to claim 1, wherein heat conducting layers are arranged on two sides of the heating wire layer, and the heat conducting layers are copper foils; and a glue film layer is paved on the contact surfaces of the heating wire film, the electrode patch and the front edge skin.
6. The electrically heated icebreaker wing skin structure of claim 1, further comprising an upper skin and a lower skin, the upper and lower skins being secured to the wing skeleton, the leading edge skin being secured to the upper and lower skins.
7. The electric heating deicing machine wing skin structure according to claim 6, wherein a plurality of temperature sensors and icing sensors are arranged on the inner side of the junction of the front edge skin and the upper and lower skins, and a control unit and a heating power supply are arranged on the inner side of the machine body;
the icing sensor is used for detecting an icing area and icing degree of the outer surface of the wing skin and transmitting the icing area and icing degree to the control unit;
the temperature sensor is used for detecting the temperature of the wing skin and transmitting the temperature to the control unit;
the control unit controls the heating element to heat the icing region according to the detection result of the icing sensor, and regulates and controls the temperature of the heating element according to the detection result of the temperature sensor;
the heating power supply is used for supplying power to the heating element and sharing power with other equipment on the machine.
8. The electrically heated icebreaker wing skin structure of claim 7, wherein the icing sensor and temperature sensor operate intermittently; the control unit controls the heating element to preheat the skin at low temperature so that the temperature of the skin is higher than the icing point.
9. The forming method of the electric heating ice preventing and removing machine wing skin structure is characterized by comprising the following steps of:
preparing an electric heating wire film;
paving a plurality of fiber cloths and a glue film layer in a mold, and partitioning and arranging an electric heating wire film and an electrode patch on the glue film layer according to position requirements;
after the laying is completed, a glue film layer is laid on the surfaces of the heating wire film and the electrode patch, and the pretreated fiber cloth is laid on the heating wire film and the electrode patch to complete the laying;
and after the skin is laid, placing the wing front edge skin into an autoclave or a vacuum curing furnace to finish the curing and molding of the wing front edge skin.
10. The method of forming an electrically heated icebreaker wing skin structure of claim 9, further comprising surface blasting the heating wire film and electrode patch prior to laying; and after the front edge skin is solidified and molded, cleaning the surface of the electrode patch, and connecting a power supply cable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210695465.8A CN117284470A (en) | 2022-06-20 | 2022-06-20 | Electric heating ice machine preventing and removing wing skin structure and forming method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210695465.8A CN117284470A (en) | 2022-06-20 | 2022-06-20 | Electric heating ice machine preventing and removing wing skin structure and forming method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117284470A true CN117284470A (en) | 2023-12-26 |
Family
ID=89257661
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210695465.8A Pending CN117284470A (en) | 2022-06-20 | 2022-06-20 | Electric heating ice machine preventing and removing wing skin structure and forming method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117284470A (en) |
-
2022
- 2022-06-20 CN CN202210695465.8A patent/CN117284470A/en active Pending
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