An aircraft anti-icing device and its usage method

Abstract

The present invention discloses an anti-icing device for an aircraft and its usage method, which relates to the technical field of aircraft anti-icing. To solve the problem that when the temperature of the wing of an existing aircraft is too low and icing occurs, the temperature rise mainly relies on the high temperature generated by the engine operation. Since heat loss occurs during heat transmission, it will lead to uneven temperatures at positions farther and closer to the engine, easily causing wing deformation and even affecting the service life of the wing after a long time. An outer heating shell is arranged outside the heating device; an inner chamber, which is arranged inside the heating shell and is an integral structure with the heating shell. A partition plate is arranged inside the inner chamber, and the partition plate is welded to the heating shell; an upper air duct, which is arranged above the partition plate and is an integral structure with the inner chamber, is arranged below the partition plate; a blowing mechanism, which is arranged inside the upper air duct and the lower air duct, and a heating mechanism is arranged on every other blowing mechanism.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft anti-icing, and particularly to an aircraft anti-icing device and a using method thereof. Background Technique

[0002] When an aircraft flies to a certain altitude, the surrounding air has high humidity and low temperature, and moisture condenses on the surface of the aircraft to form water droplets. When the surface temperature of the aircraft during flight is below 0 °C, the water droplets will freeze into ice again. The ice will increase the resistance of the aircraft, deteriorate the endurance performance, and cause the airframe to vibrate, making the operation difficult, and even threatening the engine and leading to accidents. Therefore, it is necessary to heat the surface of the aircraft to avoid icing.

[0003] However, when the temperature of the existing aircraft wing is too low and ices up, the temperature rise mainly relies on the high temperature generated by the engine operation. Since heat loss occurs during heat transmission, the temperature will be uneven between positions far and near the engine, which easily causes the wing to deform and even affects the service life of the wing after a long time.

[0004] Therefore, we propose an aircraft anti-icing device and a using method thereof to solve the problems raised above. Summary of the Invention

[0005] The purpose of the present invention is to provide an aircraft anti-icing device and a using method thereof to solve the problem that when the temperature of the existing aircraft wing is too low and ices up, the temperature rise mainly relies on the high temperature generated by the engine operation. Since heat loss occurs during heat transmission, the temperature will be uneven between positions far and near the engine, which easily causes the wing to deform and even affects the service life of the wing after a long time.

[0006] To achieve the above purpose, the present invention provides the following technical solution: An aircraft anti-icing device includes a heating device, and a heating outer shell is arranged outside the heating device;

[0007] It further includes:

[0008] An inner chamber, which is arranged inside the heating outer shell and is an integral structure with the heating outer shell. A partition plate is arranged inside the inner chamber, and the partition plate is welded to the heating outer shell;

[0009] An upper air duct, which is arranged above the partition plate and is an integral structure with the inner chamber. A lower air duct is arranged below the partition plate and is an integral structure with the inner chamber;

[0010] An air supply mechanism, which is arranged inside the upper air duct and the lower air duct, and the air supply mechanism is connected to the heating outer shell by bolts. A heating mechanism is arranged on every other air supply mechanism.

[0011] Preferably, a first air blower is provided below the air supply mechanism, and the first air blower is embedded and connected to both the upper air duct and the lower air duct by bolts. A second air blower is provided above the first air blower, and the second air blower is embedded and connected to both the upper air duct and the lower air duct by bolts. A third air blower is provided above the second air blower, and the third air blower is embedded and connected to both the upper air duct and the lower air duct by bolts.

[0012] Preferably, a plurality of control fixing grooves are provided on the partition plate, and the control fixing grooves and the partition plate are of an integral structure.

[0013] Preferably, a heater is provided inside the temperature raising mechanism. A controller is provided below the heater, and the controller is embedded and connected to the control fixing groove. First electric heating rods are provided on both sides of the front end above the controller, and the first electric heating rods are embedded and electrically connected to the controller. Second electric heating rods are provided behind both sides of the first electric heating rods, and the second electric heating rods are embedded and electrically connected to the controller.

[0014] Preferably, heat conducting sheets are provided outside the first electric heating rods and the second electric heating rods. A plurality of heat conducting sheets are provided, and both the first electric heating rods and the second electric heating rods are embedded and connected to the heat conducting sheets.

[0015] Preferably, air delivery channels are provided inside the first air blower, the second air blower and the third air blower. The air delivery channels and the first air blower, the second air blower and the third air blower are of an integral structure. Air delivery motors are provided on one side inside the first air blower, the second air blower and the third air blower. An air delivery blade seat is provided outside the air delivery motor, and the air delivery blade seat is connected to the air delivery motor shaft. Air blower blades are provided outside the air delivery blade seat, and the air blower blades are welded to the air delivery blade seat.

[0016] Preferably, an air outlet is provided on one side of the air delivery channel, and the air outlet and the air delivery channel are of an integral structure. An air inlet is provided on the other side of the air delivery channel, and the air inlet and the air delivery channel are of an integral structure.

[0017] Preferably, a temperature raising sticker plate is provided at the front end of the temperature raising device, and the temperature raising sticker plate and the temperature raising device are of an integral structure. Adhesive sheets are provided on the temperature raising sticker plate, and the adhesive sheets are adhesively connected to the temperature raising sticker plate.

[0018] Preferably, a method for using an aircraft anti-icing device includes the following steps:

[0019] Step 1: Install the temperature raising device inside the aircraft wing, make the adhesive sheet fit with the front end inside the wing, start the control fixing groove when the temperature is too low, make the first electric heating rods and the second electric heating rods heat up, further make the temperature of the heat conducting sheets rise, and the heat conducting sheets raise the air temperature;

[0020] Step 2: Start the first air supply fan, the second air supply fan, and the third air supply fan, convey the air heated by the heat conducting sheet to one side, heat the interior of the temperature raising device, and then after the air temperature drops, pass through the second temperature raising mechanism to raise the air temperature again. The air is repeatedly heated in the temperature raising device, thereby increasing the temperature of the temperature raising device.

[0021] Step 3: The bonding sheet transfers the heat of the temperature raising device to the aircraft wing, raising the temperature of the wing to prevent icing.

[0022] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0023] 1. By arranging an upper air duct and a lower air duct inside the temperature raising device, and arranging a temperature raising mechanism and an air supply mechanism inside the upper air duct and the lower air duct, the present invention can heat the temperature inside the upper air duct and the lower air duct through the temperature raising mechanism, and then make the air circulate inside the upper air duct and the lower air duct through the air supply mechanism to evenly heat the temperature raising outer shell. Then, through the heat conducting silicone sheet bonding sheet, the temperature of the temperature raising outer shell is transmitted to the external aircraft wing to evenly heat the wing, avoiding the problem that when the temperature of the existing aircraft wing is too low and icing occurs, the temperature rise mainly relies on the high temperature generated by the engine operation. Since heat loss occurs during heat transmission, the temperature at positions far from the engine and positions close to the engine will be uneven, easily causing wing deformation and even affecting the service life of the wing after a long time.

[0024] 2. By arranging a controller, a first electric heating rod, a second electric heating rod, and a heat conducting sheet inside the temperature raising mechanism, after starting the controller, the first electric heating rod and the second electric heating rod can be controlled to heat. The heat conducting sheet transfers the heat of the first electric heating rod and the second electric heating rod to itself, and then transfers the heat to the external air, so that when the air supply fan blade rotates, the heated air can be taken away and circulated inside the temperature raising outer shell to heat the temperature raising outer shell, further increasing the temperature of the wing to prevent icing from causing aircraft failure or even accidents. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 is the front view structural schematic diagram of the present invention;

[0026] Figure 2 is the internal structural schematic diagram of the present invention;

[0027] Figure 3 is the side view sectional structural schematic diagram of the present invention;

[0028] Figure 4 is the structural schematic diagram of the temperature raising mechanism of the present invention;

[0029] Figure 5 is the partial enlarged view at A of the present invention;

[0030] In the figure: 1. Heating device; 2. Heating outer shell; 3. Inner bin; 4. Partition board; 5. Upper air duct; 6. Lower air duct; 7. Heating mechanism; 8. Air supply mechanism; 9. First air supply fan; 10. Second air supply fan; 11. Third air supply fan; 12. Air supply blade seat; 13. Air supply motor; 14. Air supply fan blade; 15. Heater; 16. Controller; 17. First electric heating rod; 18. Second electric heating rod; 19. Heat conducting sheet; 20. Air delivery channel; 21. Air outlet; 22. Air inlet; 23. Heating patch board; 24. Fitting piece; 25. Control fixing groove. Specific embodiments

[0031] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments.

[0032] Please refer to Figures 1-5 , an embodiment provided by the present invention: an anti-icing device for an aircraft, including a heating device 1, and a heating outer shell 2 is arranged outside the heating device 1;

[0033] It further includes:

[0034] An inner bin 3, which is arranged inside the heating outer shell 2, and the inner bin 3 and the heating outer shell 2 are of an integral structure. A partition board 4 is arranged inside the inner bin 3, and the partition board 4 is welded to the heating outer shell 2;

[0035] An upper air duct 5, which is arranged above the partition board 4, and the upper air duct 5 and the inner bin 3 are of an integral structure. It is arranged below the partition board 4, and the lower air duct 6 and the inner bin 3 are of an integral structure;

[0036] An air supply mechanism 8, which is arranged inside the upper air duct 5 and the lower air duct 6, and the air supply mechanism 8 is connected to the heating outer shell 2 by bolts. A heating mechanism 7 is arranged on every other air supply mechanism 8. The heating mechanism 7 can heat the air, and then the air is transported by the air supply mechanism 8, so that the air circulates inside the heating outer shell 2, uniformly heating the heating outer shell 2. The heating outer shell 2 then transfers the heat to the external wing, avoiding the problem that when the temperature of the existing aircraft wing is too low and freezes, the heating mainly relies on the high temperature generated by the engine operation. Since heat loss will occur during the heat transfer, the temperature at positions far from the engine and positions close to the engine will be uneven, which is likely to cause the wing to deform, and even affect the service life of the wing after a long time.

[0037] Please refer to Figures 2-3, a first air blower 9 is arranged below the air supply mechanism 8, and the first air blower 9 is embedded and connected to both the upper air duct 5 and the lower air duct 6 by bolts. A second air blower 10 is arranged above the first air blower 9, and the second air blower 10 is embedded and connected to both the upper air duct 5 and the lower air duct 6 by bolts. A third air blower 11 is arranged above the second air blower 10, and the third air blower 11 is embedded and connected to both the upper air duct 5 and the lower air duct 6 by bolts. The three air blowers convey the hot air, avoiding the problem of slow air flow and uneven temperature rise caused by too few air blowers.

[0038] Please refer to Figures 3-4 , a plurality of control fixing grooves 25 are arranged on the partition plate 4, and the control fixing grooves 25 and the partition plate 4 are of an integral structure. The control fixing grooves 25 can fix the controller 16 to avoid the heating mechanism 7 malfunctioning due to vibration.

[0039] Please refer to Figures 3-4 , a heater 15 is arranged inside the heating mechanism 7, and a controller 16 is arranged below the heater 15. The controller 16 is embedded and connected to the control fixing groove 25. On both sides of the front end above the controller 16, first electric heating rods 17 are arranged, and the first electric heating rods 17 are embedded and electrically connected to the controller 16. Second electric heating rods 18 are arranged behind both sides of the first electric heating rods 17, and the second electric heating rods 18 are embedded and electrically connected to the controller 16. After the controller 16 is started, the first electric heating rods 17 and the second electric heating rods 18 can be powered on, and the two heat up to heat the air.

[0040] Please refer to Figure 4 , heat conduction sheets 19 are arranged outside the first electric heating rods 17 and the second electric heating rods 18, and a plurality of heat conduction sheets 19 are arranged. Both the first electric heating rods 17 and the second electric heating rods 18 are embedded and connected to the heat conduction sheets 19. The heat conduction sheets 19 can transfer the heat of the first electric heating rods 17 and the second electric heating rods 18 to themselves, dispersing the heat. At the same time, the heat conduction sheets 19 have a large contact area with the air and can quickly transfer the heat to a large amount of air to quickly heat up and avoid the wing from icing.

[0041] Please refer to Figure 3 and 5, an air delivery channel 20 is provided inside each of the first air delivery fan 9, the second air delivery fan 10 and the third air delivery fan 11, and the air delivery channels 20 are respectively an integral structure with the first air delivery fan 9, the second air delivery fan 10 and the third air delivery fan 11. An air delivery motor 13 is provided on one side inside each of the first air delivery fan 9, the second air delivery fan 10 and the third air delivery fan 11. An air delivery blade seat 12 is provided outside the air delivery motor 13, and the air delivery blade seat 12 is axially connected to the air delivery motor 13. An air delivery fan blade 14 is provided outside the air delivery blade seat 12, and the air delivery fan blade 14 is welded to the air delivery blade seat 12. The air delivery motor 13 is arranged inside the air delivery blade seat 12. After being started, it can drive the air delivery blade seat 12 to rotate, reducing the volume of the first air delivery fan 9, the second air delivery fan 10 and the third air delivery fan 11 and avoiding affecting the flow of hot air.

[0042] Please refer to Figure 5 , an air outlet 21 is provided on one side of the air delivery channel 20, and the air outlet 21 is an integral structure with the air delivery channel 20. An air inlet 22 is provided on the other side of the air delivery channel 20, and the air inlet 22 is an integral structure with the air delivery channel 20. Filters are provided inside both the air outlet 21 and the air inlet 22 to prevent foreign objects from contacting the internal components and causing malfunctions.

[0043] Please refer to Figure 1 and 3 , a heating sticker plate 23 is provided at the front end of the heating device 1, and the heating sticker plate 23 is an integral structure with the heating device 1. A bonding piece 24 is provided on the heating sticker plate 23, and the bonding piece 24 is adhesively connected to the heating sticker plate 23. The bonding piece 24 is a silicone heat-conducting sticker, which can better fit with the wing to fully conduct the heat of the heating outer shell 2 to the wing and avoid the problem of partial icing caused by uneven wing heating.

[0044] Please refer to Figures 1-5 , a usage method of an aircraft anti-icing device includes the following steps:

[0045] Step 1: Install the heating device 1 inside the aircraft wing, make the bonding piece 24 fit with the front end inside the wing, and start the control fixing groove 25 when the temperature is too low to heat the first electric heating rod 17 and the second electric heating rod 18, further increasing the temperature of the heat-conducting piece 19, and the heat-conducting piece 19 raises the air temperature;

[0046] Step 2: Start the first air delivery fan 9, the second air delivery fan 10 and the third air delivery fan 11 to deliver the air heated by the heat-conducting piece 19 to one side to heat the inside of the heating device 1. After the air temperature drops, it passes through the second heating mechanism 7 to heat the air again. The air is repeatedly heated inside the heating device 1, thereby increasing the temperature of the heating device 1;

[0047] Step 3: The bonding piece 24 transfers the heat of the heating device 1 to the aircraft wing, so that the temperature of the wing rises to avoid icing.

[0048] For those skilled in the art, it is obvious that the present invention is not limited to the details of the above-described exemplary embodiments, and the present invention can be implemented in other specific forms without departing from the spirit or basic characteristics of the present invention. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be embraced within the present invention. Any reference signs in the claims should not be construed as limiting the claims involved.

Claims

1. An anti-icing device for an aircraft, comprising a heating device (1), and a heating outer shell (2) is arranged outside the heating device (1); It is characterized in that: It further comprises: An inner chamber (3), which is arranged inside the heating outer shell (2), and the inner chamber (3) and the heating outer shell (2) are of an integral structure. A partition plate (4) is arranged inside the inner chamber (3), and the partition plate (4) is welded to the heating outer shell (2); An upper air duct (5), which is arranged above the partition plate (4), and the upper air duct (5) and the inner chamber (3) are of an integral structure. A lower air duct (6) is arranged below the partition plate (4), and the lower air duct (6) and the inner chamber (3) are of an integral structure; An air supply mechanism (8), which is arranged inside the upper air duct (5) and the lower air duct (6), and the air supply mechanism (8) is connected to the heating outer shell (2) by bolts. A heating mechanism (7) is arranged on every other air supply mechanism (8).

2. The anti-icing device for an aircraft according to claim 1, characterized in that: A first air supply fan (9) is arranged below the air supply mechanism (8), and the first air supply fan (9) is embedded and connected to the upper air duct (5) and the lower air duct (6) by bolts. A second air supply fan (10) is arranged above the first air supply fan (9), and the second air supply fan (10) is embedded and connected to the upper air duct (5) and the lower air duct (6) by bolts. A third air supply fan (11) is arranged above the second air supply fan (10), and the third air supply fan (11) is embedded and connected to the upper air duct (5) and the lower air duct (6) by bolts.

3. The anti-icing device for an aircraft according to claim 1, characterized in that: A plurality of control fixing grooves (25) are arranged on the partition plate (4), and the control fixing grooves (25) and the partition plate (4) are of an integral structure.

4. An aircraft anti-icing device according to claim 1, characterized in that: A heater (15) is arranged inside the heating mechanism (7). A controller (16) is arranged below the heater (15), and the controller (16) is embedded and connected to the control fixing groove (25). First electric heating rods (17) are arranged on both sides of the front end above the controller (16), and the first electric heating rods (17) are embedded and electrically connected to the controller (16). Second electric heating rods (18) are arranged behind both sides of the first electric heating rods (17), and the second electric heating rods (18) are embedded and electrically connected to the controller (16).

5. The anti-icing device for an aircraft according to claim 4, characterized in that: Heat conducting sheets (19) are arranged outside the first electric heating rods (17) and the second electric heating rods (18), and a plurality of heat conducting sheets (19) are provided. The first electric heating rods (17) and the second electric heating rods (18) are both embedded and connected to the heat conducting sheets (19).

6. The anti-icing device for an aircraft according to claim 2, characterized in that: An air delivery channel (20) is provided inside each of the first air delivery fan (9), the second air delivery fan (10) and the third air delivery fan (11), and the air delivery channels (20) and the first air delivery fan (9), the second air delivery fan (10) and the third air delivery fan (11) are of an integral structure. An air delivery motor (13) is provided on one side inside each of the first air delivery fan (9), the second air delivery fan (10) and the third air delivery fan (11). An air delivery blade seat (12) is provided outside the air delivery motor (13), and the air delivery blade seat (12) is connected to the air delivery motor (13) by a shaft. An air delivery fan blade (14) is provided outside the air delivery blade seat (12), and the air delivery fan blade (14) is connected to the air delivery blade seat (12) by welding.

7. An anti-icing device for an aircraft according to claim 6, characterized in that: An air outlet (21) is provided on one side of the air delivery channel (20), and the air outlet (21) and the air delivery channel (20) are of an integral structure. An air inlet (22) is provided on the other side of the air delivery channel (20), and the air inlet (22) and the air delivery channel (20) are of an integral structure.

8. The anti-icing device for an aircraft according to claim 1, characterized in that: A heating patch plate (23) is provided at the front end of the heating device (1), and the heating patch plate (23) and the heating device (1) are of an integral structure. A fitting piece (24) is provided on the heating patch plate (23), and the fitting piece (24) is adhesively connected to the heating patch plate (23).

9. A method for using an aircraft anti-icing device, implemented based on the aircraft anti-icing device according to any one of claims 1-8, characterized in that, It includes the following steps: Step 1: Install the heating device (1) inside the aircraft wing, make the fitting piece (24) fit with the front end inside the wing, start the control fixing groove (25) when the temperature is too low, so that the first heating rod (17) and the second heating rod (18) are heated, further increase the temperature of the heat conducting sheet (19), and the heat conducting sheet (19) increases the air temperature; Step 2: Start the first air delivery fan (9), the second air delivery fan (10) and the third air delivery fan (11), deliver the air heated by the heat conducting sheet (19) to one side, heat the inside of the heating device (1), and after the air temperature drops, pass through the second heating mechanism (7) to heat the air again. The air is repeatedly heated inside the heating device (1), so as to increase the temperature of the heating device (1); Step 3: The fitting piece (24) transfers the heat of the heating device (1) to the aircraft wing to increase the temperature of the wing and prevent icing.

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