Air cooling heat dissipation structure of vertical take-off and landing aircraft

Abstract

The utility model relates to the technical field of air cooling heat dissipation, and discloses a vertical take-off and landing aircraft air cooling heat dissipation structure which comprises a battery shell, a heat dissipation opening is formed in the battery shell, an integrated fan is fixedly installed in the heat dissipation opening, and a first dustproof hole is located above the integrated fan. The air inlet is formed in the aircraft bottom plate, meanwhile, the rotating shaft is rotationally connected into the air inlet, the second fan blades are fixedly installed on the outer side of the rotating shaft, airflow can enter the air inlet, at the moment, the airflow can blow the second fan blades to drive the rotating shaft to rotate rapidly, and the airflow can make contact with the bottom of the battery shell; and the fan blades I drive the rotating shaft to rotate along with the airflow direction, so that the air temperature is reduced along with the increase of the height of the aircraft, the bottom of the battery shell can be obviously cooled, and meanwhile, the fan blades II drive the rotating shaft to rotate along with the airflow direction, so that the effect of not increasing the flight resistance of the aircraft is achieved while heat dissipation is performed.

Description

Technical Field

[0001] The utility model relates to the technical field of air cooling and heat dissipation, and more specifically, to an air cooling and heat dissipation structure for a vertical take-off and landing aircraft. Background Art

[0002] Existing aircraft usually refer to electric aircraft, which have simple structures and are easy to manufacture, with light motors, smooth rotation, and easy-to-standardize power systems. However, electric aircraft batteries dissipate a large amount of heat and need to rely on active cooling devices. Existing air-cooled heat dissipation devices mostly add multiple vents during the heat dissipation process and use the airflow during flight to cool down. These vents greatly increase the flight resistance of the aircraft, require sacrificing a higher speed of the aircraft, and have a poor cooling effect. Utility Model Content

[0003] In order to overcome the deficiencies of the prior art, the utility model provides an air-cooling heat dissipation structure for a vertical take-off and landing aircraft, which has the advantage of not increasing the flight resistance of the aircraft.

[0004] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a vertical take-off and landing aircraft air-cooling heat dissipation structure, comprising a battery shell, a heat dissipation port is provided inside the battery shell, an integrated fan is fixedly installed inside the heat dissipation port, an air intake groove is provided inside the integrated fan, a fan blade is provided inside the integrated fan, the fan blade is located at the top of the battery shell, a slide groove is provided inside the battery shell, a slider is slidably connected inside the slide groove, a dust cover is fixedly installed above the slider, a dust hole is provided at the top of the dust cover, and the dust hole is located above the integrated fan.

[0005] As an optimal technical solution of the present invention, a screw hole is opened inside the battery shell, a bolt is engaged inside the screw hole, a connecting block is sleeved on the outside of the bolt, the connecting block is located above the battery shell and the connecting block is fixedly connected to the dust cover.

[0006] As an optimal technical solution of the present invention, a second slide groove is provided inside the battery housing, a baffle is slidably connected inside the second slide groove, a second dustproof hole is provided inside the baffle, and the second dustproof hole is located in the front of the battery housing.

[0007] As an optimal technical solution of the present invention, a limiting column 1 is fixedly installed on the top of the battery housing, and a limiting sleeve is sleeved inside the limiting column 1. A fixed column 2 is fixedly installed in front of the baffle, and the internal sleeve of the fixing column 2 is sleeved at one end away from the limiting column 1, and the limiting sleeve has a certain elasticity.

[0008] As an optimal technical solution of the present invention, the bottom of the battery housing is fixedly connected to a connecting plate, the bottom of the connecting plate is fixedly installed with an aircraft base plate, an air inlet is opened inside the aircraft base plate, the inside of the air inlet is rotatably connected to a rotating shaft, and a fan blade 2 is fixedly installed on the outside of the rotating shaft.

[0009] As a preferred technical solution of the present invention, there are four rotating shafts, all of which are located inside the air inlet; there are multiple fan blades 2, and the multiple fan blades 2 are respectively located outside the four rotating shafts.

[0010] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0011] 1. The utility model opens an air inlet inside the bottom plate of the aircraft, and a rotating shaft is rotatably connected inside the air inlet, and a second fan blade is fixedly installed on the outside of the rotating shaft. When the aircraft is in normal flight, airflow will enter the inside of the air inlet. At this time, the airflow will blow the second fan blade to drive the rotating shaft to rotate rapidly, and the airflow will contact the bottom of the battery casing. As the altitude of the aircraft increases, the temperature of the air will decrease, which can significantly cool the bottom of the battery casing. At the same time, the second fan blade drives the rotating shaft to rotate in the direction of the airflow. Therefore, while dissipating heat, the flight resistance of the aircraft will not be increased.

[0012] 2. The utility model provides a second slide groove inside the battery housing, a baffle is slidably connected inside the second slide groove, and a second dustproof hole is provided inside the baffle. When the aircraft flies for a long time, it is inevitable that it will encounter areas with greater pollution and more dust. At this time, the second dustproof hole will block the dust to achieve a dustproof effect. At the same time, the interiors of the first limiting column and the second fixing column are respectively connected to the two ends of the limiting sleeve. The limiting sleeve contacts the battery housing and the baffle, thereby fixing the baffle. After the limiting sleeve is removed, the baffle can be removed by sliding with the second slide groove, thereby achieving the effect of convenient disassembly and cleaning. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a schematic diagram of the overall structure of the utility model;

[0014] Figure 2 For this utility model Figure 1 A magnified schematic diagram of the structure at A;

[0015] Figure 3 It is a partial structural diagram of the utility model;

[0016] Figure 4 For this utility model Figure 2 A magnified schematic diagram of the structure at B;

[0017] Figure 5 This is a schematic diagram of the air inlet structure of the utility model.

[0018] In the figure: 1. Battery casing; 2. Heat dissipation vent; 3. Integrated fan; 4. Air intake slot; 5. Blade 1; 6. Slide slot 1; 7. Slider; 8. Dust cover; 9. Dust hole 1; 10. Connecting block; 11. Bolt; 12. Screw hole; 13. Slide slot 2; 14. Baffle; 15. Dust hole 2; 16. Limit column 1; 17. Limit sleeve; 18. Fixed column 2; 19. Connecting plate; 20. Aircraft bottom plate; 21. Air intake; 22. Rotating shaft; 23. Blade 2. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0020] like Figures 1 to 5 As shown, the utility model provides an air-cooled heat dissipation structure for a vertical take-off and landing aircraft, including a battery housing 1, a heat dissipation port 2 is provided inside the battery housing 1, an integrated fan 3 is fixedly installed inside the heat dissipation port 2, an air intake slot 4 is provided inside the integrated fan 3, a fan blade 5 is provided inside the integrated fan 3, the fan blade 5 is located at the top of the battery housing 1, a slide groove 6 is provided inside the battery housing 1, a slider 7 is slidably connected inside the slide groove 6, a dust cover 8 is fixedly installed above the slider 7, a dust hole 9 is provided at the top of the dust cover 8, and the dust hole 9 is located above the integrated fan 3.

[0021] The integrated fan 3 can be self-starting. When the aircraft is hovering, the integrated fan 3 starts to drive the fan blade 5 to rotate rapidly, thereby accelerating the circulation of air through the fan blade 5, thereby quickly cooling the interior of the battery casing 1. At the same time, the dust cover 8 has a certain protective effect on the integrated fan 3.

[0022] Among them, a screw hole 12 is opened inside the battery shell 1, and a bolt 11 is engaged inside the screw hole 12. A connecting block 10 is sleeved on the outside of the bolt 11. The connecting block 10 is located above the battery shell 1 and is fixedly connected to the dust cover 8.

[0023] The connecting block 10 is engaged with the screw hole 12 through the bolt 11, so that the dust cover 8 is fixed, thereby providing overall stability of the dust cover 8. At the same time, after the bolt 11 is removed and adjusted, the dust cover 8 can be easily disassembled, achieving the effect of convenient maintenance and cleaning.

[0024] A second slide groove 13 is provided inside the battery housing 1 , a baffle 14 is slidably connected inside the second slide groove 13 , a second dustproof hole 15 is provided inside the baffle 14 , and the second dustproof hole 15 is located in the front of the battery housing 1 .

[0025] There are multiple dustproof holes 15. The main function of the multiple dustproof holes 15 is to prevent dust from entering the battery housing 1 while ensuring ventilation and heat dissipation. When the aircraft flies in an area with greater pollution, dust is easily accumulated. At this time, the dustproof holes 15 are blocked, thereby improving the overall service life of the battery housing 1.

[0026] Among them, a limiting column 16 is fixedly installed on the top of the battery housing 1, and a limiting sleeve 17 is sleeved inside the limiting column 16. A fixing column 2 18 is fixedly installed in front of the baffle 14, and the fixing column 2 18 is sleeved inside the limiting sleeve 17 away from the end of the limiting column 16. The limiting sleeve 17 has a certain elasticity.

[0027] The limiting sleeve 17 is L-shaped. When both ends are respectively sleeved on the outer sides of the limiting column 16 and the fixing column 2 18, the baffle 14 is limited, thereby preventing the baffle 14 from shaking during flight.

[0028] Among them, the bottom of the battery shell 1 is fixedly connected to a connecting plate 19, the bottom of the connecting plate 19 is fixedly installed with an aircraft base plate 20, an air inlet 21 is opened inside the aircraft base plate 20, the inside of the air inlet 21 is rotatably connected to a rotating shaft 22, and a fan blade 23 is fixedly installed on the outside of the rotating shaft 22.

[0029] The air inlet 21 is located directly below the battery housing 1. When the aircraft is flying, air passes through the inside of the air inlet 21 and comes into contact with the bottom of the battery housing 1. At the same time, the higher the position, the lower the stability of the air flow will be. Therefore, when the air flow passes through, it will have a certain cooling effect on the bottom of the battery housing 1.

[0030] There are four rotating shafts 22 , all of which are located inside the air inlet 21 . There are multiple second fan blades 23 , each of which is located outside the four rotating shafts 22 .

[0031] When the aircraft is flying normally, the airflow passes through the inside of the air inlet 21, blowing the fan blade 23 to rotate at high speed, so that the airflow will contact the top of the air inlet 21. At the same time, the airflow will be accelerated, thereby increasing the cooling effect on the bottom of the battery housing 1. At the same time, since the fan blade 23 will drive the rotating shaft 22 to rotate in the direction of the airflow, the effect of not increasing resistance can be achieved.

[0032] The working principle and use process of this utility model:

[0033] First, install the dust cover 8 by sliding the slider 7 and the slide groove 6 so that the dust cover 8 is located above the integrated fan 3. At the same time, the bolts 11 are engaged with the screw holes 12, thereby fixing the dust cover 8 through the connecting block 10.

[0034] Next, the baffle 14 is installed to the front of the battery housing 1 by sliding with the second slide groove 13, and then the two ends of the limiting sleeve 17 are respectively inserted into the outer sides of the limiting column 16 and the fixing column 2 18 to fix the baffle 14 in place and prevent the baffle 14 from shaking;

[0035] At this time, when the aircraft is in normal flight, airflow will enter the interior of the air inlet 21, and the airflow will blow the second fan blade 23 to drive the rotating shaft 22 to rotate rapidly, and the airflow will contact the bottom of the battery housing 1. As the altitude of the aircraft increases, the temperature of the air will decrease, thereby significantly cooling the bottom of the battery housing 1. At the same time, the second fan blade 23 drives the rotating shaft 22 to rotate in the direction of the airflow, so that while dissipating heat, it will not increase the flight resistance of the aircraft.

[0036] Finally, since the integrated fan 3 can be self-started, when the aircraft is hovering, the integrated fan 3 starts and drives the fan blade 5 to rotate rapidly, thereby accelerating the circulation of air through the fan blade 5, thereby quickly cooling the interior of the battery housing 1. At the same time, the dust cover 8 has a certain protective effect on the integrated fan 3.

[0037] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

[0038] Although the embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A vertical take-off and landing aircraft air-cooling heat dissipation structure, comprising a battery housing (1), characterized in that: The battery housing (1) is provided with a heat dissipation vent (2), an integrated fan (3) is fixedly installed inside the heat dissipation vent (2), an air inlet groove (4) is provided inside the integrated fan (3), a fan blade (5) is provided inside the integrated fan (3), and the fan blade (5) is located at the top of the battery housing (1), a slide groove (6) is provided inside the battery housing (1), a slider (7) is slidably connected inside the slide groove (6), a dust cover (8) is fixedly installed above the slider (7), a dust hole (9) is provided at the top of the dust cover (8), and the dust hole (9) is located above the integrated fan (3).

2. The air-cooling heat dissipation structure for a vertical take-off and landing aircraft according to claim 1, characterized in that: A screw hole (12) is provided inside the battery housing (1), a bolt (11) is engaged inside the screw hole (12), a connecting block (10) is sleeved on the outside of the bolt (11), the connecting block (10) is located above the battery housing (1), and the connecting block (10) and the dust cover (8) are fixedly connected.

3. The air-cooling heat dissipation structure for a vertical take-off and landing aircraft according to claim 1, characterized in that: A second slide groove (13) is provided inside the battery housing (1), a baffle (14) is slidably connected inside the second slide groove (13), a second dustproof hole (15) is provided inside the baffle (14), and the second dustproof hole (15) is located in front of the battery housing (1).

4. The air-cooling heat dissipation structure for a vertical take-off and landing aircraft according to claim 3, characterized in that: A limiting column 1 (16) is fixedly installed above the battery housing (1), and a limiting sleeve (17) is sleeved inside the limiting column 1 (16). A fixing column 2 (18) is fixedly installed in front of the baffle (14), and an end of the limiting sleeve (17) is sleeved inside the fixing column 2 (18) away from the limiting column 1 (16). The limiting sleeve (17) has a certain elasticity.

5. The air-cooling heat dissipation structure for a vertical take-off and landing aircraft according to claim 1, characterized in that: The bottom of the battery housing (1) is fixedly connected to a connecting plate (19), the bottom of the connecting plate (19) is fixedly mounted with an aircraft base plate (20), an air inlet (21) is provided inside the aircraft base plate (20), a rotating shaft (22) is rotatably connected inside the air inlet (21), and a second fan blade (23) is fixedly mounted on the outer side of the rotating shaft (22).

6. The air-cooling heat dissipation structure for a vertical take-off and landing aircraft according to claim 5, characterized in that: There are four rotating shafts (22), and the four rotating shafts (22) are all located inside the air inlet (21). There are multiple fan blades (23), and the multiple fan blades (23) are respectively located outside the four rotating shafts (22).

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