High-speed unmanned aerial vehicle with heat dissipation function

Abstract

The invention discloses a high-speed unmanned aerial vehicle with a heat dissipation function, and relates to the technical field of unmanned aerial vehicles, the high-speed unmanned aerial vehicle comprises a top cabin cover mounted on one side of a main shell, and an opening for placing a lens body is formed in the end part of the main shell. According to the high-speed unmanned aerial vehicle with the heat dissipation function, the air inlet amount of the head of the unmanned aerial vehicle is adjusted through the air guide mechanism according to the flight state of the unmanned aerial vehicle, the situation that the real-time flight state is affected by too large or too small air inlet amount is avoided, the unmanned aerial vehicle can maintain the stable flight speed and posture, and meanwhile heat dissipation is promoted through cooperation with the opening and closing mechanism; the air inlet is formed, so that airflow can enter the tail cabin cover in a concentrated mode, the airflow is collected and compressed, meanwhile, the electric strip heater heats the airflow, hot air flowing can simulate the effect of compressed air to a certain degree, larger thrust is generated through heating and air compressing, air breaking can be better achieved, and the air breaking effect is improved. The air resistance is reduced, so that the flight speed is increased.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a high-speed UAV with heat dissipation function. Background Technology

[0002] A drone is an aircraft capable of autonomous flight or remote control, widely used in various fields. It typically consists of an airframe, power system, sensors, and control system. Drones can be equipped with cameras, lidar, and other devices depending on their needs, for applications such as logistics, military reconnaissance, and emergency rescue. Drones primarily fly in two ways: fixed-wing and rotary-wing. Fixed-wing drones are suitable for long-duration cruises, while rotary-wing drones offer greater flexibility and are suitable for low-altitude flight and hovering.

[0003] Patent publication number CN206552252U describes a special-purpose drone with anti-drone capabilities. It includes a drone body, a camera mounted on the drone body, and a drone countermeasure device. The anti-drone device comprises an omnidirectional antenna, a jamming signal generator, a power supply, a controller, and a protective housing. The omnidirectional antenna, jamming signal generator, and power supply are housed within the protective housing. The camera, power supply, and jamming signal generator are connected to the controller, and the jamming signal generator is connected to the omnidirectional antenna. This special-purpose drone, equipped with anti-drone technology, can counter other drones from all directions using its omnidirectional antenna. Because drones can fly at relatively high altitudes, this special-purpose drone completely overcomes the limitations of other low-altitude countermeasure devices.

[0004] Based on the aforementioned existing patents, it is known that the fuselage of existing drones is usually in a closed state, with airflow flowing along the outside of the fuselage, which creates a certain amount of air resistance for the drone. This limits the maximum flight speed of the drone to a certain range, resulting in a low overall flight speed. The simple shape of the fuselage cannot efficiently guide the airflow, causing the internal components to overheat and reducing heat dissipation performance. At the same time, uneven airflow distribution during flight can affect flight stability. Therefore, we propose a high-speed drone with heat dissipation function. Summary of the Invention

[0005] The purpose of this invention is to provide a high-speed unmanned aerial vehicle (UAV) with heat dissipation function to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a high-speed unmanned aerial vehicle with heat dissipation function, including a top cover installed on one side of the main shell, an opening for placing a lens body at the end of the main shell, a carbon plate installed at the end of the main shell away from the lens body, a tail cover connected to the side of the carbon plate away from the main shell, and an integrally formed wing plate mounting cover provided on the side of the main shell and the top cover away from each other.

[0007] The tail hatch is equipped with an electric rod fixing component for fixing the electric rod. The electric rod is an electric rod heater composed of resistance wires. The outer surfaces of both sides of the main shell are provided with concave air guide grooves. The tail hatch is provided with inclined air inlets on both sides of the tail hatch that are in the same position as the air guide grooves. The narrower end of the tail hatch is provided with a tail air outlet for air discharge.

[0008] The inner side of the wing plate mounting cover is provided with a guide wing to improve flight stability. The air guide mechanism works in conjunction with the opening and closing mechanism to adjust the size of the air intake channel while stabilizing flight.

[0009] Furthermore, a lens fixing component is installed at the opening of the main shell to limit the position of the lens body, and an image transmission fixing component for supporting the image transmission module is snapped onto the inner wall of the main shell below the lens fixing component. A fixing ring for guiding air inlet is connected below the image transmission fixing component.

[0010] Furthermore, the inner side of the fixed ring is provided with an air guide mechanism for adjusting the size of the air intake channel, the inside of the wing plate mounting cover is provided with an opening and closing mechanism for driving the guide wing to open and close stably, and one end of the opening and closing mechanism is located inside the main shell and the top hatch. The four ends of the carbon plate are all equipped with propeller assemblies for driving the overall flight.

[0011] The main shell has an electrical control assembly installed on its inner wall in the middle. A GPS mounting bracket for placing a GPS sensor is installed on the inner wall of the main shell away from the electrical control assembly. A flight control mounting ring for fixing the flight control module is installed at the center of the tail hatch. The electrical strip mounting bracket is located below the flight control mounting ring.

[0012] Furthermore, the air guiding mechanism includes a first opening located in the middle of the fixed ring, and a second opening arranged in a ring around the inner side of the fixed ring surrounding the first opening.

[0013] Furthermore, an adjusting disc is movably sleeved in the middle of the fixed ring, and annularly distributed air inlets No. 1 and No. 2 are provided on the inner side of the adjusting disc to adjust the airflow.

[0014] Furthermore, one side of the adjusting disc is provided with a rotating ring located outside the fixed ring, and the two sides of the rotating ring are connected with equally spaced annularly distributed toothed blocks.

[0015] Furthermore, the opening and closing mechanism includes a traction rod that slides through the inside of the wing plate mounting cover. Both the main shell and the top hatch are provided with turntables on the inner side near the traction rod, and the main shell and the turntables are connected by a bearing structure.

[0016] Furthermore, a motor is installed on the inner wall of the top hatch and connected to the turntable by a coupling. An eccentric traction block for driving the sliding extension and retraction of the traction rod is fixed on the surface of the turntable. The turntable and the toothed block are meshing.

[0017] Furthermore, the inner side of the traction rod is provided with a strip groove for the traction block to slide, and the inner cavity of the wing plate mounting cover is fixed with a rotating shaft that is movably connected to the guide wing.

[0018] Furthermore, the traction block is fixed with a pull block that pulls the guide vane to deflect at one end near the guide vane, and the surface of the guide vane located on one side of the rotating shaft is provided with an opening and closing groove with one end raised. The pull block and the opening and closing groove are connected by a sliding connection structure.

[0019] Compared with the prior art, the beneficial effects of the present invention are:

[0020] 1. This high-speed drone with heat dissipation function adjusts the air intake at the drone's head through an air guide mechanism according to the drone's flight status. This avoids excessive or insufficient air intake affecting the real-time flight status, which helps the drone maintain a stable flight speed and attitude. Furthermore, the airflow contacts the internal components, carrying away the heat generated by the components. At the same time, the opening and closing mechanism drives the air guide wing to adjust to a scissor state, which enables the airflow to be evenly distributed around the fuselage, reducing local heat accumulation caused by poor airflow. By improving the uniformity and fluidity of the airflow, the scissor state of the air guide wing can promote the effective exchange between cold and hot air.

[0021] 2. This high-speed UAV with heat dissipation function has an air inlet that allows airflow to be concentrated into the tail canopy, where it is compressed and then heated by an electric heater. This increases the internal energy of the air, raising its temperature. The density of the hot air is reduced, but it expands faster. This hot air flow simulates the effect of compressed air to some extent. By heating and compressing the air, it generates greater thrust, which helps to break through the wind better, reduces air resistance, and thus increases flight speed.

[0022] 3. This high-speed drone with heat dissipation function has a scissor-like deflector that allows the drone to effectively manage airflow during ascent. The deflector reduces pitch instability caused by rapid ascent, ensuring the drone maintains a stable attitude during ascent. Furthermore, the scissor-like deflector helps the drone better resist lateral winds during flight, reducing instability caused by wind and ensuring the drone's controllability and safety during high-speed flight. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0024] Figure 2 This is a schematic diagram of the overall exploded structure of the present invention;

[0025] Figure 3 This is a schematic diagram of the top hatch structure of the present invention;

[0026] Figure 4 This is a schematic diagram of the main shell structure of the present invention;

[0027] Figure 5 This is a schematic diagram of the tail hatch structure of the present invention;

[0028] Figure 6 This is a schematic diagram of the air inlet structure of the present invention;

[0029] Figure 7 This is a schematic diagram of the propeller assembly structure of the present invention;

[0030] Figure 8 This is a schematic diagram of the fixing ring structure of the present invention;

[0031] Figure 9 This is a schematic diagram of the adjusting disc structure of the present invention;

[0032] Figure 10 This is a schematic diagram of the air guide mechanism of the present invention;

[0033] Figure 11 This is a schematic diagram of the opening and closing mechanism of the present invention;

[0034] Figure 12 This is a schematic diagram of the air guide wing structure of the present invention;

[0035] Figure 13 This is a schematic diagram of the internal structure of the wing plate mounting cover of the present invention.

[0036] In the diagram: 1. Main hull; 2. Top hatch; 3. Lens body; 4. Wing plate mounting cover; 5. Carbon fiber plate; 6. Tail hatch; 7. Propeller assembly; 8. Air guide mechanism; 801. No. 1 port; 802. No. 2 port; 803. Adjustment disc; 804. No. 1 air vent; 805. Rotary ring; 9. Guide vane; 10. Lens mounting component; 11. Image transmission mounting component; 12. Fixing ring; 13. Power control... Components; 14. GPS mounting hardware; 15. Flight controller mounting ring; 16. Battery mounting hardware; 17. Opening and closing slot; 18. Opening and closing mechanism; 1801. Tow bar; 1802. Strip groove; 1803. Tow block; 1804. Turntable; 19. Motor; 20. Tail exhaust vent; 21. Air guide duct; 22. Air inlet; 23. Second air outlet; 24. Tooth block; 25. Rotating shaft; 26. Pull block. Detailed Implementation

[0037] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0038] Please see Figures 1-7 The present invention provides a technical solution: a high-speed unmanned aerial vehicle with heat dissipation function, including a top cover 2 installed on one side of the main shell 1, an opening for placing a lens body 3 at the end of the main shell 1, a lens fixing component 10 for limiting the lens body 3 installed at the opening of the main shell 1, a carbon plate 5 installed at the end of the main shell 1 away from the lens body 3, a tail cover 6 connected to the side of the carbon plate 5 away from the main shell 1, and propeller assemblies 7 for driving the overall flight installed at each of the four ends of the carbon plate 5.

[0039] In practice, during the flight of the drone, the lens body 3 captures images, the lens fixing component 10 limits the lens body 3, the carbon plate 5 is used to connect the main shell 1 and the tail hatch 6, and the propeller assembly 7 rotates to drive the drone to fly.

[0040] See Figures 1-3 and Figure 6 It can be seen that the inner wall of the main shell 1 located below the lens fixing component 10 is fitted with an image transmission fixing component 11 for supporting the image transmission module. The middle inner wall of the main shell 1 is equipped with a power control component 13. The inner wall of the main shell 1 away from the power control component 13 is equipped with a GPS fixing component 14 for placing a GPS sensor. The center of the tail hatch 6 is equipped with a flight control mounting ring 15 for fixing the flight control module.

[0041] In practice, the power control component 13 is electrically connected to the internal components of the UAV via power wires to ensure that each component can obtain the required power. The image transmission module is installed on the image transmission mounting component 11. The image transmission module is responsible for wirelessly transmitting the video or image signals captured by the UAV to the ground. The GPS sensor is installed on the GPS mounting component 14. The GPS sensor is used to receive satellite signals to determine the geographical location of the UAV. The flight control module is installed on the flight control mounting ring 15. The flight control module is responsible for processing the data from each sensor and controlling the flight attitude, speed and direction of the UAV.

[0042] See Figures 1-3 and Figures 7-11It can be seen that the main shell 1 and the top hatch 2 are provided with an integrally formed wing plate mounting cover 4 on the side away from each other. The lower part of the image transmission fixing component 11 is connected to a fixing ring 12 for guiding the air intake. The inner side of the fixing ring 12 is provided with an air guiding mechanism 8 for adjusting the size of the air intake channel. The air guiding mechanism 8 includes a first opening 801 opened in the middle of the fixing ring 12. The inner side of the fixing ring 12 around the first opening 801 is provided with a second opening 802 distributed in a ring.

[0043] An adjusting disc 803 is movably sleeved in the middle of the fixed ring 12. The inner side of the adjusting disc 803 is provided with a first air inlet 804 and a second air inlet 23 that are distributed in a ring to adjust the airflow. A rotating ring 805 is provided on one side of the adjusting disc 803, located outside the fixed ring 12. The rotation of the rotating ring 805 drives the fixed ring 12 to rotate, thereby causing the fixed ring 12 to drive the first air inlet 804 and the second air inlet 23 to rotate, adjusting the position of the first air inlet 804 and the second air inlet 23. The two sides of the rotating ring 805 are connected with equally spaced ring-distributed toothed blocks 24.

[0044] In practice, when the drone is in flight, the airflow enters the main shell 1 through the opening at the lens body 3, then enters the fixing ring 12 through the opening at the image transmission fixing component 11, and then passes through the first opening 801 and the second opening 802 on the inner side of the fixing ring 12 to enter the interior of the main shell 1, where it comes into contact with the internal components. The airflow carries away the heat generated by the components, and finally the airflow is discharged from the tail cover 6, which reduces air resistance and facilitates high-speed flight.

[0045] The air intake of the fixed ring 12 can be adjusted according to the flight status. During the ascent from a stationary state, the air intake can be increased. Since the diameter of the first air inlet 804 is larger than that of the second air inlet 23, the adjusting plate 803 is rotated inside the fixed ring 12 by the rotating ring 805. This causes the adjusting plate 803 to align the first air inlet 804 with the second air inlet 802, facilitating the passage of a large amount of airflow, promoting the rapid ascent of the drone, and reducing air resistance. During level flight, the air intake can be reduced appropriately. The adjusting plate 803 aligns the second air inlet 23 with the second air inlet 802, reducing the diameter of the air intake channel and preventing a large amount of airflow from passing through. This helps the drone maintain a stable flight speed and attitude.

[0046] See Figure 1 , Figure 2 and Figures 5-7It can be seen that concave air guide grooves 21 are provided on both outer surfaces of the main shell 1. Air inlets 22, which are inclined and allow airflow to enter, are provided on both sides of the tail cover 6, which are in the same position as the air guide grooves 21. An air outlet 20 for air outlet is provided at the narrower end of the tail cover 6. An electric bar fixing member 16 for fixing electric bars is provided inside the tail cover 6 below the flight control mounting ring 15. The electric bar is an electric bar heater composed of resistance wires.

[0047] In practice, during the flight of the UAV, the main shell 1 first comes into contact with the flowing airflow. The airflow flows along the outer wall of the main shell 1 and is guided by the concave air guide groove 21, allowing the airflow to enter the air inlet 22 along the air guide groove 21. Subsequently, the airflow flows along the air inlet 22 and comes into contact with the electric strip heater on the electric strip fixing member 16 in the tail cover 6. The setting of the air inlet 22 allows the airflow to be concentrated and enter the tail cover 6, where the airflow is gathered and compressed. At the same time, the electric strip heater heats the airflow, increasing the internal energy of the air and thus raising the temperature of the gas. The density of the high-temperature gas will decrease, but the gas will expand faster. This hot air flow will simulate the effect of compressed gas to a certain extent. By heating and compressing the air, greater thrust is generated, which can better break the wind, reduce air resistance, and thus increase the flight speed.

[0048] See Figures 1-4 , Figure 7 and Figures 11-13 It is known that the inner side of the wing plate mounting cover 4 is provided with a guide wing 9 to improve flight stability, and the inside of the wing plate mounting cover 4 is equipped with an opening and closing mechanism 18 for driving the guide wing 9 to open and close stably, and one end of the opening and closing mechanism 18 is located inside the main shell 1 and the top hatch 2.

[0049] In practice, the guide wing 9 can effectively reduce the disturbance of airflow to the fuselage by changing the flow pattern of airflow around the UAV fuselage, reduce turbulence and instability factors, thereby improving the flight stability of the UAV. In addition, the opening and closing mechanism 18 dynamically adjusts the guide wing 9 to adapt to different flight states.

[0050] See Figure 3 , Figure 4 , Figure 8 and Figures 10-13It is known that the opening and closing mechanism 18 includes a traction rod 1801 that slides through the inner side of the wing plate mounting cover 4, and the traction rod 1801 passes through the inner wall of the main shell 1 and the top cover 2. The main shell 1 and the top cover 2 are both provided with turntables 1804 near the inner side of the traction rod 1801. The main shell 1 and the turntable 1804 are connected by a bearing structure. The inner wall of the top cover 2 is equipped with a motor 19 that is connected to the turntable 1804 by a coupling. The surface of the turntable 1804 is fixed with an eccentric traction block 1803 for driving the traction rod 1801 to slide and extend. The turntable 1804 and the toothed block 24 are connected by a meshing structure.

[0051] The inner side of the traction rod 1801 is provided with a strip groove 1802 for the traction block 1803 to slide. The inner cavity of the wing plate mounting cover 4 is fixed with a rotating shaft 25 that is movably connected to the guide wing 9. The end of the traction block 1803 near the guide wing 9 is fixed with a pull block 26 that pulls the guide wing 9 to deflect. The surface of the guide wing 9 located on the side of the rotating shaft 25 is provided with an opening and closing groove 17 that is raised at one end. The pull block 26 and the opening and closing groove 17 are slidably connected.

[0052] In specific implementation, the motor 19 drives the turntable 1804 to rotate. The turntable 1804 meshes with the toothed block 24, causing the turntable 1804 to drive the rotating ring 805 to rotate. While adjusting the size of the air duct, the turntable 1804 drives the traction block 1803 to rotate eccentrically, causing the traction block 1803 to slide in the strip groove 1802. As a result, the traction block 1803 drives the traction rod 1801 to extend and slide. The other end of the traction rod 1801 drives the pull block 26 to slide laterally. The pull block 26 slides in the opening and closing groove 17 and squeezes the inclined surface of the opening and closing groove 17, causing one end of the guide vane 9 to rotate around the rotating shaft 25 to open or close, adjusting the position of the guide vane 9.

[0053] By operating the opening and closing mechanism 18 and the air guide mechanism 8 simultaneously, the heat dissipation can be improved while the flight stability is enhanced. During ascent, the air intake channel at the head of the main shell 1 is enlarged and the two air guides 9 are opened in a scissor-like state. Since the motor and other electronic components generate a lot of heat during ascent, enlarging the air intake channel will allow more air to flow into the interior of the UAV, enhancing airflow and carrying away more heat. Furthermore, the air guides 9 in the scissor-like state can make the airflow evenly distributed around the fuselage, reducing local heat accumulation caused by poor airflow. By improving the uniformity and flowability of the airflow, the scissor-like state of the air guides 9 can promote the effective exchange between cold and hot air.

[0054] Meanwhile, the scissor-shaped deflector 9, when deployed, allows the drone to effectively manage airflow during ascent, reducing pitch instability caused by rapid ascent and ensuring stable attitude during the ascent. Furthermore, the scissor-shaped deflector 9 helps the drone better resist lateral winds, reducing instability caused by wind and ensuring the drone's controllability and safety during high-speed flight.

[0055] In summary, when using this high-speed UAV with heat dissipation function, the power control component 13 is electrically connected to the internal components of the UAV through power wires to ensure that each component can obtain the required power normally. The image transmission module is installed on the image transmission mounting component 11. The image transmission module is responsible for wirelessly transmitting the video or image signals captured by the UAV to the ground. The GPS sensor is installed on the GPS mounting component 14. The GPS sensor is used to receive satellite signals to determine the geographical location of the UAV. The flight control module is installed on the flight control mounting ring 15. The flight control module is responsible for processing the data from various sensors and controlling the flight attitude, speed and direction of the UAV. At the same time, the air duct 21, the air guiding mechanism 8, the electric strip heater and the tail air outlet 20 concentrate the airflow to improve heat dissipation and generate greater inertia by heating and compressing the air, thereby increasing the flight speed. At the same time, the position of the air guide wing 9 is adjusted in real time through the opening and closing mechanism 18 to help the UAV better resist the wind from the side and reduce the instability caused by the wind. This ensures the controllability and safety of the UAV during high-speed flight. The contents not described in detail in this specification are existing technologies known to those skilled in the art.

Claims

1. A high-speed unmanned aerial vehicle (UAV) with heat dissipation function, characterized in that: Including the top hatch (2) installed on one side of the main shell (1), the end of the main shell (1) is provided with an opening for placing the lens body (3), the end of the main shell (1) away from the lens body (3) is provided with a carbon plate (5), the side of the carbon plate (5) away from the main shell (1) is connected with the tail hatch (6), the side of the main shell (1) and the top hatch (2) away from each other is provided with an integrally formed wing plate mounting cover (4). The inside of the tail hatch (6) is provided with an electric strip fixing part (16) for fixing the electric strip, the electric strip is an electric strip heater composed of resistance wire, the outer surface of the two sides of the main shell (1) is provided with a concave air guide groove (21), the two sides of the tail hatch (6) at the same position as the air guide groove (21) are provided with an inclined air inlet (22) for air inflow, and the narrower end of the tail hatch (6) is provided with a tail air outlet (20) for air outflow. The inside of the wing plate mounting cover (4) is provided with a flow guide wing (9) for improving flight stability, the air guide mechanism (8) is matched with the opening and closing mechanism (18) to adjust the size of the air inlet channel while stabilizing flight.

2. The high-speed unmanned aerial vehicle with heat dissipation function according to claim 1, characterized in that: The opening of the main shell (1) is provided with a lens fixing part (10) for limiting the lens body (3), the inner wall of the main shell (1) below the lens fixing part (10) is clamped with an image transmission fixing part (11) for supporting the image transmission module, and the lower side of the image transmission fixing part (11) is connected with a fixed ring (12) for guiding air inflow.

3. The high-speed unmanned aerial vehicle with heat dissipation function according to claim 2, characterized in that: The inside of the fixed ring (12) is provided with an air guide mechanism (8) for adjusting the size of the air inlet channel, the inside of the wing plate mounting cover (4) is provided with an opening and closing mechanism (18) for driving the flow guide wing (9) to stably open and close, one end of the opening and closing mechanism (18) is located on the inside of the main shell (1) and the top hatch (2), and the four ends of the carbon plate (5) are provided with propeller assemblies (7) for driving the whole flight. The middle inner wall of the main shell (1) is provided with a power control assembly (13), the inner wall of the main shell (1) away from the power control assembly (13) is provided with a GPS fixing part (14) for placing a GPS sensor, the center of the tail hatch (6) is provided with a flight control mounting ring (15) for fixing a flight control module, and the electric strip fixing part (16) is located below the flight control mounting ring (15).

4. The high-speed unmanned aerial vehicle with heat dissipation function according to claim 2, characterized in that: The air guide mechanism (8) comprises a first through hole (801) formed in the middle of the fixed ring (12), and a plurality of second through holes (802) are formed in the inside of the fixed ring (12) around the first through hole (801).

5. The high-speed unmanned aerial vehicle with heat dissipation function according to claim 4, characterized in that: The middle of the fixed ring (12) movably sleeves a adjusting disc (803), the inside of the adjusting disc (803) is provided with a plurality of first air inlets (804) and second air inlets (23) for adjusting air inflow.

6. The high-speed unmanned aerial vehicle with heat dissipation function according to claim 5, characterized in that: One side of the adjusting disc (803) is provided with a rotating ring (805) located outside the fixed ring (12), and the two sides of the rotating ring (805) are connected with a plurality of tooth blocks (24) distributed in an equidistant annular manner.

7. The high-speed unmanned aerial vehicle with heat dissipation function according to claim 2, characterized in that: The opening and closing mechanism (18) comprises a traction rod (1801) sliding through the inside of the wing plate mounting cover (4), the main shell (1) and the top hatch (2) are provided with rotating discs (1804) near the inside of the traction rod (1801), and the main shell (1) and the rotating disc (1804) are connected in a bearing connection structure.

8. The high-speed unmanned aerial vehicle with heat dissipation function according to claim 7, characterized in that: A motor (19) connected with the rotating disc (1804) in a shaft coupling structure is mounted on the inner wall of the top hatch (2), the surface of the rotating disc (1804) is fixed with an eccentric traction block (1803) for driving the traction rod (1801) to slide and stretch, and the rotating disc (1804) and the tooth block (24) are connected in a meshing connection structure.

9. The high-speed unmanned aerial vehicle with heat dissipation function according to claim 8, characterized in that: The inside of the traction rod (1801) is provided with a strip-shaped slot (1802) for the sliding of the traction block (1803), and the inside cavity of the wing plate mounting cover (4) is fixed with a rotating shaft (25) movably sleeved with the guide vane (9).

10. The high-speed unmanned aerial vehicle with heat dissipation function according to claim 9, characterized in that: One end of the traction block (1803) near the guide vane (9) is fixed with a pulling block (26) for pulling the deflection of the guide vane (9), the surface of the guide vane (9) on one side of the rotating shaft (25) is provided with an opening and closing slot (17) in a one-end-up state, and the pulling block (26) and the opening and closing slot (17) are connected in a sliding connection structure.

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