Cooling arm of unmanned aerial vehicle

Abstract

The invention provides an unmanned aerial vehicle heat dissipation vehicle arm, and relates to the technical field of unmanned aerial vehicles, the unmanned aerial vehicle heat dissipation vehicle arm comprises a mounting frame, a switching mechanism, a transmission mechanism and a vehicle arm assembly, a motor is mounted at the top of the switching mechanism, a fixing plate is integrally formed at the top end of the mounting frame, and the mounting frame is screwed to the side edge of an unmanned aerial vehicle body through the fixing plate; transmission mechanisms are welded to the outer sides of the mounting frames, two vehicle arm assemblies are arranged on the surface of each mounting frame, the end of each vehicle arm assembly is embedded into the inner side of the corresponding mounting frame, and electric adjusting plates are in threaded connection with the interiors of shells of the vehicle arm assemblies; in the normal flight process, cooling and heat dissipation treatment can be carried out on the electric speed controller plate on the inner side of each vehicle arm without the help of an extra power system, airflow flowing of the rotor wings is not disturbed or flight resistance is not increased, and the rapid steering function is achieved by means of the internal heat dissipation fan; even if one of the arms breaks down, stable flight can be achieved, and progress and development of the aviation equipment industry are promoted.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicle (UAV) aviation equipment, and particularly to a heat-dissipating arm for a UAV. Background Art

[0002] The arm of a UAV is a commonly used device in aviation equipment and is used to complete the operation of the equipment carried by the UAV. Generally, the UAV arm consists of three parts: a bottom connecting part, a support arm, and an end effector. As an important part of the UAV, the UAV arm is also a relatively mature technology in the aviation equipment industry. Key components such as circuit boards and motors may be installed inside it. These components generate a large amount of heat during operation. If the heat cannot be dissipated in time, it will cause the temperature of the components to rise, thereby affecting the performance and stability of the UAV.

[0003] When dissipating heat from the UAV arm in the prior art, heat dissipation can be directly completed by mounting an independent cooling fan at the bottom. However, this solution consumes additional energy during operation, resulting in a reduced endurance of the UAV body. On the other hand, the number of rotors of a conventional UAV is fixed. Once any one of the rotors fails during flight, it will immediately cause the UAV to tilt, resulting in a significant decrease in stability and even directly causing damage to the entire UAV. Summary of the Invention

[0004] Aiming at the deficiencies of the prior art, the purpose of the present invention is to provide a heat-dissipating arm for a UAV to solve the problems raised in the above background art. During normal flight, the present invention can achieve the cooling and heat dissipation treatment of the electronic speed controller board on the inner side of each arm without relying on an additional power system, and will not interfere with the airflow of the rotors or increase the flight resistance. With the help of the internal cooling fan, it can achieve a fast steering function, and the UAV can still fly stably even if one of the arms fails.

[0005] To achieve the above purpose, the present invention is realized through the following technical solutions: A heat-dissipating arm for a UAV includes an arm body. The arm body includes a mounting frame, a switching mechanism, a transmission mechanism, and an arm assembly. A motor is installed on the top of the switching mechanism. The top of the mounting frame is integrally formed with a fixing plate, and the mounting frame is screwed to the side of the UAV body through the fixing plate. The transmission mechanism is welded to the outside of the mounting frame. Two arm assemblies are arranged on the surface of each mounting frame, and the end of each arm assembly is embedded inside the mounting frame. An electronic speed controller board is screwed inside the housing of the arm assembly, and a rotor is installed at the end of the arm assembly. The switching mechanism and the motor are both installed at the middle position of the fuselage of the UAV body. The side of the switching mechanism is connected to a part of the transmission mechanism through a toothed belt. The edge of the transmission mechanism is inserted into the surface of the arm assembly. The installation heights of adjacent two arm assemblies are different.

[0006] Furthermore, the mounting bracket includes a mounting plate, a top-layer sliding groove, and a bottom-layer sliding groove. The top-layer sliding groove and the bottom-layer sliding groove are both opened in the outer area of the mounting plate. Arc-shaped rods are inserted into the interiors of the top-layer sliding groove and the bottom-layer sliding groove. A through hole is opened in the middle of the mounting plate.

[0007] Furthermore, an extension plate is integrally formed at the top of the mounting plate, and a fixing plate is integrally formed at the top of the extension plate. The top-layer sliding groove and the bottom-layer sliding groove are separated by a partition plate. The through hole is opened in the middle area of the partition plate.

[0008] Furthermore, the arm assembly includes a support arm, an ESC board, and a rotor. A transmission groove is opened on the surface of the support arm. A middle heat dissipation net is opened on the support arm opposite to the ESC board, and a side heat dissipation net is opened on one side of the middle heat dissipation net.

[0009] Furthermore, a cooling fan is installed on the other side of the middle heat dissipation net. The cooling fan blows air flow into the area of the side heat dissipation net from the outside. A sliding sleeve is opened at the end of the support arm. The sliding sleeve is sleeved on the surface of the arc-shaped rod. The end of the support arm is embedded into the inner side of the top-layer sliding groove or the bottom-layer sliding groove.

[0010] Furthermore, a heat conduction frame is integrally formed at the other end of the support arm. A heat conduction net is laid on the surface of the heat conduction frame. The rotor is installed on the top of the heat conduction frame. A diversion port is opened at the end of the support arm. The inner space of the heat conduction frame is connected to the surrounding space of the ESC board through the diversion port.

[0011] Furthermore, the switching mechanism includes a motor and a transmission box. The motor is screwed to the top end of the transmission box. A driving gear, a large transmission gear, and a small transmission gear are installed inside the transmission box. A driving shaft is inserted into the output end of the motor. The driving shaft and the driving gear are connected by a flat key.

[0012] Furthermore, the number of the large transmission gears is four, and each large transmission gear meshes with the driving gear. The small transmission gear is integrally formed at the top of the large transmission gear. A toothed belt is sleeved on the side of each small transmission gear.

[0013] Furthermore, the transmission mechanism includes a transmission sleeve, a transmission disc, and a driven gear. The transmission sleeve is welded on the surface of the through hole. The toothed belt passes through the inside of the transmission sleeve. The transmission disc is fixed at the end of the transmission sleeve. A notch is opened on the side of the transmission disc, and a slot is opened in the middle of the housing of the transmission disc.

[0014] Furthermore, snap rings are integrally formed on the top and bottom surfaces of the driven gear. A linkage plate is integrally formed in the middle of the snap ring. A plug post is provided at the end of the linkage plate. A limiting convex disk is integrally formed on the surface of the plug post. The plug post and the limiting convex disk are both embedded inside the transmission groove. The linkage plate passes outwards from the notch. A support shaft is inserted on the surface of the linkage plate. The support shaft is embedded inside the slot.

[0015] Advantages of the present invention:

[0016] 1. During the normal flight of the UAV heat dissipation arm, with the help of the heat conduction structure at the bottom, the heat generated at the ESC board inside the arm is guided towards the bottom of the rotor, and the heat dissipation effect is directly achieved through the airflow generated by the rotor itself. Therefore, under normal heat dissipation conditions, it is possible to cool the ESC board inside each arm without increasing additional energy consumption.

[0017] 2. In this UAV heat dissipation arm, two arm components are installed on the UAV body as a group. With the help of the internal cooling fan, a thrust in the horizontal direction can be applied to achieve a quick turning function, reducing the control difficulty, providing an additional heat dissipation effect, and being able to achieve two rotational movement functions in the clockwise and counterclockwise directions.

[0018] 3. For this UAV heat dissipation arm, with the help of the switching mechanism and the transmission mechanism, the two arm components can be regulated to achieve the switching function between an eight-rotor and a four-rotor. Therefore, during flight, an emergency plan for any arm failure is provided, improving the safety and reliability of the entire UAV flight, and promoting the progress and development of the aviation equipment industry. Description of the Drawings

[0019] Figure 1 It is a schematic structural diagram of the outer shape of a UAV heat dissipation arm of the present invention;

[0020] Figure 2 It is a schematic structural diagram of the mounting frame part of the present invention;

[0021] Figure 3 It is a schematic structural diagram of the arm component part of the present invention;

[0022] Figure 4 It is an exploded view of the arm component of the present invention;

[0023] Figure 5 It is a top view inside the switching mechanism of the present invention;

[0024] Figure 6 It is a schematic structural diagram of the transmission mechanism part of the present invention;

[0025] Figure 7 It is an internal structural diagram of the transmission mechanism of the present invention;

[0026] In the figure: 1, mounting bracket; 2, switching mechanism; 3, transmission mechanism; 4, arm assembly; 5, motor; 6, mounting plate; 7, extension plate; 8, fixing plate; 9, top layer chute; 10, bottom layer chute; 11, arc-shaped rod; 12, partition board; 13, through hole; 14, support arm; 15, sliding sleeve; 16, transmission slot; 17, middle heat dissipation net; 18, side heat dissipation net; 19, support shaft; 20, rotor; 21, heat conduction frame; 22, heat dissipation fan; 23, electronic speed control board; 24, shunt port; 25, heat conduction net; 26, drive shaft; 27, driving gear; 28, large transmission gear; 29, small transmission gear; 30, toothed belt; 31, transmission sleeve; 32, transmission disc; 33, notch; 34, slot; 35, driven gear; 36, snap ring; 37, linkage plate; 38, insertion column; 39, limit convex disc. Specific embodiments

[0027] In order to make the technical means, creative features, achieved purposes and functions of the present invention easy to understand, the present invention will be further described below in conjunction with specific embodiments.

[0028] Please refer to Figures 1 to 7 , the present invention provides the following technical solutions: An unmanned aerial vehicle heat dissipation arm, including an arm body, the arm body includes a mounting bracket 1, a switching mechanism 2, a transmission mechanism 3 and an arm assembly 4, a motor 5 is installed on the top of the switching mechanism 2, a fixing plate 8 is integrally formed at the top end of the mounting bracket 1, and the mounting bracket 1 is screwed to the side of the unmanned aerial vehicle body through the fixing plate 8. A transmission mechanism 3 is welded on the outside of the mounting bracket 1. Two arm assemblies 4 are arranged on the surface of each mounting bracket 1, and the end of each arm assembly 4 is embedded in the inner side of the mounting bracket 1. An electronic speed control board 23 is screwed inside the shell of the arm assembly 4, and a rotor 20 is installed at the end of the arm assembly 4. The switching mechanism 2 and the motor 5 are both installed at the middle position of the fuselage of the unmanned aerial vehicle body. The side of the switching mechanism 2 is connected to a part of the transmission mechanism 3 through a toothed belt 30. The edge of the transmission mechanism 3 is inserted into the surface of the arm assembly 4. The installation heights between two adjacent arm assemblies 4 are different. This unmanned aerial vehicle heat dissipation arm is used to be installed on the unmanned aerial vehicle body, provide power drive, and has its own heat dissipation effect.

[0029] When the present invention is installed, the switching mechanism 2 therein is installed at the middle position of the outer shell of the UAV body, and a plurality of arm assemblies 4 are supported and installed through installation. The two arm assemblies 4 connected to the same mounting frame 1 are connected through a transmission mechanism 3, and the transmission mechanism 3 is controlled by the switching mechanism 2. When performing flight control, the operation of the transmission mechanism 3 can be controlled by means of the switching mechanism 2, so as to control the rotation of the two arm assemblies 4 connected to the same mounting frame 1, so that the two arm assemblies 4 can be unfolded or overlapped on the same vertical plane. Therefore, after a total of four sets of such arm modules are installed on the UAV body, two flight states of quadcopter 20 or octocopter 20 drive can be realized through the switching mechanism 2. During the flight process, the heat dissipation function is realized by means of the internal structure of each support arm 14 in cooperation with the rotor 20 body, or the heat dissipation performance is further enhanced through the self-contained heat dissipation structure, and the horizontal steering function can also be provided based on the independent heat dissipation module.

[0030] [[ID=**3**]]In this embodiment, the mounting frame 1 includes a mounting plate 6, a top layer chute 9 and a bottom layer chute 10. The top layer chute 9 and the bottom layer chute 10 are both opened in the outer area of the mounting plate 6. Arc-shaped rods 11 are inserted into the interiors of the top layer chute 9 and the bottom layer chute 10. A through hole 13 is opened in the middle of the mounting plate 6. An extension plate 7 is integrally formed at the top of the mounting plate 6, a fixing plate 8 is integrally formed at the top of the extension plate 7, the top layer chute 9 and the bottom layer chute 10 are separated by a partition plate 12, and the through hole 13 is opened in the middle area of the partition plate 12. Taking two arm assemblies 4 as a group and installing them on the UAV body, the horizontal thrust can be applied by means of the internal cooling fan 22 to realize the quick steering function, reduce the operation difficulty, provide an additional heat dissipation effect, and can realize the two rotational movement functions of clockwise and counterclockwise.

[0031] [[ID=**6**]]Specifically, after each mounting frame 1 is installed on the UAV body through the extension plate 7 and the fixing plate 8 at the top, the two arm assemblies 4 can be synchronously installed on the UAV body. Each arm assembly 4 is embedded into the corresponding top layer chute 9 or bottom layer chute 10, and the two arm assemblies 4 can be controlled to be folded or unfolded in cooperation with the transmission mechanism 3, so as to achieve the purpose of switching between the quadcopter 20 and the octocopter 20.

[0032] In this embodiment, the arm assembly 4 includes a support arm 14, an ESC board 23, and a rotor 20. A transmission groove 16 is formed on the surface of the support arm 14. A middle heat dissipation net 17 is formed on the support arm 14 opposite to the ESC board 23, and a side heat dissipation net 18 is formed on one side of the middle heat dissipation net 17. A heat dissipation fan 22 is installed on the other side of the middle heat dissipation net 17. The heat dissipation fan 22 blows air into the area towards the side heat dissipation net 18 from the outside. A sliding sleeve 15 is formed at the end of the support arm 14. The sliding sleeve 15 is sleeved on the surface of the arc-shaped rod 11. The end of the support arm 14 is embedded in the inner side of the top layer chute 9 or the bottom layer chute 10. The other end of the support arm 14 is integrally formed with a heat conduction frame 21. A heat conduction net 25 is laid on the surface of the heat conduction frame 21. The rotor 20 is installed on the top of the heat conduction frame 21. A diversion port 24 is formed at the end of the support arm 14. The inner space of the heat conduction frame 21 is communicated with the surrounding space of the ESC board 23 through the diversion port 24. During normal flight, the heat generated at the ESC board 23 inside the arm is guided towards the bottom of the rotor 20 by means of the heat conduction structure at the bottom, and the heat dissipation effect is directly achieved through the airflow generated by the rotor 20 itself. Therefore, the ESC board 23 inside each arm can be cooled and dissipated without additional energy consumption under normal heat dissipation conditions.

[0033] Specifically, during normal flight, the heat dissipation fan 22 is not started. The airflow generated by partial rotation of the rotor 20 passes through the inside of the heat conduction frame 21 at the bottom. The heat conduction frame 21 is directly connected to the part of the ESC board 23 inside the support arm 14. Therefore, after the ESC board 23 transfers the heat to the inside of the heat conduction frame 21, the heat dissipation effect of the heat conduction frame 21 can be accelerated by means of the blowing effect of the rotor 20, and then the heat dissipation effect on the part of the ESC board 23 can be achieved. At the same time, the air pressure difference is directly utilized through the diversion port 24 to extract the hot air flow around the ESC board 23 towards the inner area of the heat conduction frame 21, further improving the heat dissipation performance.

[0034] Or by starting the heat dissipation fan 22, the low-temperature airflow is directly blown into the surrounding of the ESC board 23 from the outside and discharged from the side heat dissipation net 18 on the other side, and multiple heat dissipation processes can be achieved. And during this process, since the airflow is blown out from the side heat dissipation net 18, a one-way pushing effect can be provided to the support arm 14. With this pushing effect, the entire drone can be controlled to rotate in a single direction. Since there are two arm assemblies 4 on each mounting frame 1 and the heat dissipation fans 22 on the two arm assemblies 4 are installed in opposite directions, the clockwise and counterclockwise rotation functions of the drone can be achieved.

[0035] In this embodiment, the switching mechanism 2 includes a motor 5 and a transmission case. The motor 5 is screwed to the top of the transmission case. Inside the transmission case, a driving gear 27, a large transmission gear 28 and a small transmission gear 29 are installed. The output end of the motor 5 is inserted with a driving shaft 26, and the driving shaft 26 and the driving gear 27 are connected by a flat key. The number of the large transmission gears 28 is four, and each large transmission gear 28 meshes with the driving gear 27. The small transmission gear 29 is integrally formed on the top of the large transmission gear 28, and a toothed belt 30 is sleeved on the side of each small transmission gear 29.

[0036] Specifically, after starting the motor 5, the driving shaft 26 is controlled to rotate through the motor 5, and then the driving gear 27 is controlled to operate. The driving gear 27 directly drives the four groups of driven large gears on the side to rotate. Therefore, the driven small gears can drive the corresponding toothed belts 30 to move synchronously, and the independent transmission mechanisms 3 on each arm are controlled by the rotation of the toothed belts 30, so as to achieve the purpose of switching the states of the two arm assemblies 4 on each mounting bracket 1.

[0037] In this embodiment, the transmission mechanism 3 includes a transmission sleeve 31, a transmission disc 32 and a driven gear 35. The transmission sleeve 31 is welded to the surface of the through hole 13. The toothed belt 30 passes through the inside of the transmission sleeve 31. The transmission disc 32 is fixed to the end of the transmission sleeve 31. A notch 33 is formed on the side of the transmission disc 32, and a slot 34 is formed in the middle of the housing of the transmission disc 32. Snap rings 36 are integrally formed on the top and bottom surfaces of the driven gear 35. A linkage plate 37 is integrally formed in the middle of the snap rings 36. A plug post 38 is provided at the end of the linkage plate 37. A limit convex disc 39 is integrally formed on the surface of the plug post 38. The plug post 38 and the limit convex disc 39 are both embedded into the transmission slot 16. The linkage plate 37 passes outwards from the notch 33, and a support shaft 19 is inserted into the surface of the linkage plate 37. The support shaft 19 is embedded into the slot 34. With the aid of the switching mechanism 2 and the transmission mechanism 3, the two arm assemblies 4 can be adjusted. Even if a failure occurs in one of the arms, the support mode can be switched to provide continued stable flight. Therefore, an emergency plan for any arm failure during flight is provided, improving the safety and reliability of the entire UAV flight.

[0038] After starting the motor 5 to control the operation of the switching mechanism 2, the driven gear 35 is finally driven to operate. The driven gear 35 directly moves the plug posts 38 and the limit convex discs 39 stuck on different arm assemblies 4 along the transmission slot 16 through the linkage plates 37 at the top and bottom, so as to pull the entire support arm 14. The two support arms 14 move in opposite directions, so as to pull the two rotors 20 from different positions to the overlapping area in the middle, realizing the switching process between the eight-rotor 20 and the four-rotor 20.

[0039] The foregoing has shown and described the basic principles, main features and advantages of the present invention. For a person skilled in the art, it is obvious that the present invention is not limited to the details of the above-mentioned exemplary embodiments, and without departing from the spirit or basic features of the present invention, the present invention can be implemented in other specific forms.

[0040] In addition, it should be understood that although this specification is described in terms of embodiments, not every embodiment only contains an independent technical solution. This narrative manner of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A heat dissipation arm for a drone, comprising an arm body, characterized in that: The arm body includes a mounting frame (1), a switching mechanism (2), a transmission mechanism (3) and an arm assembly (4). A motor (5) is installed at the top of the switching mechanism (2). The top end of the mounting frame (1) is integrally formed with a fixing plate (8), and the mounting frame (1) is screwed to the side of the UAV body through the fixing plate (8). The transmission mechanism (3) is welded to the outside of the mounting frame (1). Two arm assemblies (4) are arranged on the surface of each mounting frame (1), and the end of each arm assembly (4) is embedded in the inner side of the mounting frame (1). An electronic speed controller board (23) is screwed inside the housing of the arm assembly (4), and a rotor (20) is installed at the end of the arm assembly (4). The switching mechanism (2) and the motor (5) are both installed at the middle position of the fuselage of the UAV body. The side of the switching mechanism (2) is connected to a part of the transmission mechanism (3) through a toothed belt (30). The edge of the transmission mechanism (3) is inserted into the surface of the arm assembly (4), and the installation heights between two adjacent arm assemblies (4) are different.

2. The drone heat dissipation arm according to claim 1, wherein: The mounting frame (1) includes a mounting plate (6), a top layer chute (9) and a bottom layer chute (10). The top layer chute (9) and the bottom layer chute (10) are both opened in the outer area of the mounting plate (6). Arc-shaped rods (11) are inserted into the top layer chute (9) and the bottom layer chute (10). A through hole (13) is opened in the middle of the mounting plate (6).

3. The cooling arm of a drone according to claim 2, characterized in that: An extension plate (7) is integrally formed at the top of the mounting plate (6), and the fixing plate (8) is integrally formed at the top of the extension plate (7). The top layer chute (9) and the bottom layer chute (10) are separated by a partition plate (12). The through hole (13) is opened in the middle area of the partition plate (12).

4. The drone heat dissipation arm according to claim 2, wherein: The arm assembly (4) includes a support arm (14), an electronic speed controller board (23) and a rotor (20). A transmission groove (16) is opened on the surface of the support arm (14). A middle heat dissipation net (17) is opened on the support arm (14) opposite to the electronic speed controller board (23). A side heat dissipation net (18) is opened on one side of the middle heat dissipation net (17).

5. The drone heat dissipation arm according to claim 4, characterized in that: A heat dissipation fan (22) is installed on the other side of the middle heat dissipation net (17). The heat dissipation fan (22) blows air flow from the outside into the area of the side heat dissipation net (18). A sliding sleeve (15) is opened at the end of the support arm (14). The sliding sleeve (15) is sleeved on the surface of the arc-shaped rod (11). The end of the support arm (14) is embedded in the inner side of the top layer chute (9) or the bottom layer chute (10).

6. The drone heat dissipation arm according to claim 5, characterized in that: The other end of the support arm (14) is integrally formed with a heat conduction frame (21). A heat conduction net (25) is laid on the surface of the heat conduction frame (21). The rotor (20) is installed on the top of the heat conduction frame (21). A diversion port (24) is opened at the end of the support arm (14). The inner space of the heat conduction frame (21) is communicated with the surrounding space of the electronic speed controller board (23) through the diversion port (24).

7. The cooling arm of an unmanned aerial vehicle according to claim 4, wherein: The switching mechanism (2) includes a motor (5) and a transmission case. The motor (5) is screwed to the top of the transmission case. Inside the transmission case, a driving gear (27), a large transmission gear (28), and a small transmission gear (29) are installed. The output end of the motor (5) is inserted with a driving shaft (26), and the driving shaft (26) and the driving gear (27) are connected by a flat key.

8. The cooling arm of a drone according to claim 7, characterized in that: The number of the large transmission gears (28) is four, and each large transmission gear (28) meshes with the driving gear (27). The small transmission gear (29) is integrally formed on the top of the large transmission gear (28). A toothed belt (30) is sleeved on the side of each small transmission gear (29).

9. The cooling arm of a drone according to claim 7, characterized in that: The transmission mechanism (3) includes a transmission sleeve (31), a transmission disc (32), and a driven gear (35). The transmission sleeve (31) is welded to the surface of the through hole (13). The toothed belt (30) passes through the inside of the transmission sleeve (31). The transmission disc (32) is fixed to the end of the transmission sleeve (31). A notch (33) is formed on the side of the transmission disc (32), and a slot (34) is formed in the middle of the housing of the transmission disc (32).

10. The cooling arm of a drone according to claim 9, characterized in that: Snap rings (36) are integrally formed on the top and bottom surfaces of the driven gear (35). A linkage plate (37) is integrally formed in the middle of the snap rings (36). An insertion column (38) is provided at the end of the linkage plate (37). A limit convex disc (39) is integrally formed on the surface of the insertion column (38). The insertion column (38) and the limit convex disc (39) are both embedded into the inside of the transmission groove (16). The linkage plate (37) passes outwards from the notch (33). A support shaft (19) is inserted into the surface of the linkage plate (37), and the support shaft (19) is embedded into the inside of the slot (34).

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