A drone and flight system

Abstract

This invention relates to the field of unmanned aerial vehicle (UAV) technology and discloses a UAV and its flight system. The UAV includes a casing, a propeller, a heat-generating component, a heat sink, and an arm assembly. One end of the arm assembly is connected to the casing, and the other end of the arm assembly is equipped with a propeller. A receiving chamber is formed inside the casing, and the heat sink and the heat-generating component are disposed within the receiving chamber, with the heat sink close to or in contact with the heat sink. An air inlet channel is formed at one end of the arm assembly, with the air inlet port located below the propeller and within the propeller's rotation area. The air outlet port of the air inlet channel communicates with the receiving chamber, and the receiving chamber has an air outlet. By forming an air inlet channel at one end of the arm assembly, and with the air inlet port located below the propeller and within the propeller's rotation area, the propeller's rotation area does not overlap with the casing, preventing wasted propeller lift and improving the UAV's flight efficiency and endurance.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV and its flight system. Background Technology

[0002] A drone is a non-manned aerial vehicle controlled by radio remote control equipment or a remote control device to perform tasks. In recent years, drones have been widely used and developed in many fields. The motherboard inside a drone contains a large number of electronic components, which are prone to overheating.

[0003] In related technologies, air inlets and outlets are typically provided on the fuselage of drones. When the drone is in flight, the propeller generates airflow that enters the drone through the air inlet and exits through the air outlet, thus dissipating heat from the internal electronic components. However, because the air inlet is located on the fuselage, there is some overlap between the propeller's rotation area and the fuselage. This results in wasted lift from the propeller, reducing the drone's flight efficiency and shortening its flight time. Summary of the Invention

[0004] The present invention aims to provide a drone and flight system to solve the technical problem that the lift of drone propellers is easily wasted in the prior art.

[0005] The technical solutions adopted by the embodiments of the present invention to solve their technical problems are as follows:

[0006] One embodiment of the present invention provides a drone, including a casing, a propeller, a heating element, a heat dissipation element, and an arm assembly;

[0007] One end of the boom assembly is connected to the housing, and the other end of the boom assembly is provided with the propeller;

[0008] The housing has a receiving chamber, and the heat dissipation component and the heat generation component are disposed in the receiving chamber, with the heat dissipation component close to or in contact with the heat generation component;

[0009] One end of the arm assembly is provided with an air inlet channel, the air inlet port of the air inlet channel is located below the propeller and within the rotation area of ​​the propeller; the air outlet port of the air inlet channel is connected to the receiving chamber, and the receiving chamber is provided with an air outlet.

[0010] In some embodiments, the air inlet port of the air inlet channel is located on the top surface of one end of the boom assembly, and the other end of the boom assembly is inclined downwards.

[0011] In some embodiments, the arm assembly includes a hinge, the receiving chamber is further provided with a connecting through hole, one end of the arm assembly is connected to the hinge, the hinge is rotatably disposed on the housing and passes through the connecting through hole;

[0012] The air inlet channel is provided inside the hinge.

[0013] In some embodiments, the hinge has an inclined surface at one end near the propeller, the inclined surface faces the propeller and forms a preset angle with the plane of rotation of the propeller, and the air inlet port of the air inlet channel passes through the inclined surface.

[0014] In some embodiments, the heat dissipation component includes a heat dissipation substrate and an air guide. The heat dissipation substrate is disposed in the receiving cavity, one side of the heat dissipation substrate faces the heat-generating component, and the air guide is disposed on the other side of the heat dissipation substrate and located at one end of the heat dissipation substrate. The other end of the heat dissipation substrate extends toward the air outlet.

[0015] The air guide has an air passage, and the air outlet of the air inlet channel is connected to the air passage.

[0016] In some embodiments, the heat sink further includes a supporting heat sink disposed within the air passage and arranged along the airflow direction of the air passage.

[0017] In some embodiments, the heat sink further includes heat sink fins, which are disposed on the other side of the heat sink substrate. One end of the heat sink fins is disposed near the air outlet of the air passage, and the other end of the heat sink fins extends toward the air outlet.

[0018] In some embodiments, the number of air guides is two, and each air guide is provided with an air passage;

[0019] The extension lines of the air outlet ports of the two air passages intersect;

[0020] The heat dissipation component also includes a guide vane, which is disposed on the other side of the heat dissipation substrate and located between the air outlet ports of the two air passages.

[0021] In some embodiments, the arm assembly includes two first arm assemblies, the propeller includes two first propellers, and the number of hinges is two;

[0022] One end of each first arm assembly is connected to a hinge, and the two hinges are respectively rotatably disposed on opposite sides of the housing and located at one end of the housing. Each hinge is provided with an air inlet channel, and the air outlet of each air inlet channel is connected to the air inlet port of a corresponding air passage. The other end of each first arm assembly is provided with a first propeller.

[0023] The number of heat dissipation fins is at least two, and an air guide channel is formed between any two adjacent heat dissipation fins. The air inlet of the air guide channel is located close to the air outlet of each air passage, and the air outlet of the air guide channel extends toward the air outlet.

[0024] In some embodiments, the arm assembly further includes two second arm assemblies, and the propeller further includes two second propellers;

[0025] One end of each of the two second arm assemblies is hinged to opposite sides of the housing and located at the other end of the housing; the other end of each second arm assembly is provided with a second propeller.

[0026] The air outlet is located at the other end of the housing and between the two second propellers.

[0027] One embodiment of the present invention also provides a flight system, the flight system including the drone described in any of the above embodiments and a remote controller, the remote controller being communicatively connected to the drone.

[0028] Compared to existing technologies, in the UAV of this invention, the fuselage is used to mount the arm assembly, the heat-generating component, and the heat-dissipating component, and a receiving chamber houses the heat-generating component and the heat-dissipating component. One end of the arm assembly is connected to the fuselage, and the other end is connected to the propeller. The heat-generating component works with the propeller to achieve the basic functions of the UAV. The airflow generated by the propeller enters the receiving chamber through the air inlet port of the air inlet channel and flows out from the air outlet, thereby dissipating heat from the heat-generating component. The heat-dissipating component improves the heat dissipation efficiency of the heat-generating component. By opening an air inlet channel at one end of the arm assembly, and with the air inlet port of the air inlet channel located below the propeller and within the propeller's rotation area, the propeller's rotation area does not overlap with the fuselage when it rotates, preventing wasted propeller lift and improving the UAV's flight efficiency and endurance.

[0029] The flight system of the present invention also has the above-mentioned advantages, which will not be repeated here. Attached Figure Description

[0030] One or more embodiments are illustrated by way of example with reference numerals in the accompanying drawings. These illustrations do not constitute a limitation on the embodiments. Elements with the same reference numerals in the drawings are denoted as similar elements. Unless otherwise stated, the figures in the drawings do not constitute a limitation on scale.

[0031] Figure 1 This is a top view of a drone in one embodiment of the present invention;

[0032] Figure 2 yes Figure 1 A cross-sectional view of a Chinese unmanned aerial vehicle (UAV);

[0033] Figure 3 yes Figure 1 A 3D view of the Chinese drone;

[0034] Figure 4 yes Figure 1 A diagram showing the connection relationships between the arm assembly, hinges, and hinge shaft of a Chinese-made UAV;

[0035] Figure 5 yes Figure 1 A schematic diagram of the deployment of the Chinese drone;

[0036] Figure 6 yes Figure 5 A magnified view of a portion of the image;

[0037] Figure 7 yes Figure 1 A partial unfolded diagram of the Chinese drone.

[0038] Figure label:

[0039] 100. Unmanned Aerial Vehicle (UAV); 10. Casing; 12. Receiving Chamber; 122. Air Outlet; 124. Connecting Through Hole; 20. Propeller; 22. First Propeller; 24. Second Propeller; 201. Rotating Area; 30. Arm Assembly; 32. First Arm Assembly; 34. Second Arm Assembly; 301. Air Inlet Channel; 40. Heat-generating Component; 50. Heat-dissipating Component; 52. Heat Dissipation Base Plate; 522. Reinforcing Rib; 54. Air Guide Component; 542. Airflow Channel; 56. Supporting Heat Dissipation Fin; 58. Heat Dissipation Fin; 582. Air Guide Channel; 59. Airflow Deflector; 60. Hinge Component; 62. Inclined Surface; 70. Hinge Shaft. Detailed Implementation

[0040] To facilitate understanding of the present invention, a more detailed description is provided below with reference to the accompanying drawings and specific embodiments. It should be noted that when an element is described as "connected" to another element, it can be directly on the other element, or one or more intermediate elements can exist between them. The terms "upper," "lower," "left," "right," "upper end," "lower end," "top," and "bottom," etc., used in this specification indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0041] Unless otherwise defined, all technical and scientific terms used in this specification have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the invention.

[0042] The following detailed description, in conjunction with all the accompanying drawings, and through specific embodiments, illustrates a drone 100 and its flight system provided in this application.

[0043] Please refer to Figures 1 to 3 One embodiment of the present invention discloses a drone 100, including a housing 10, a propeller 20, a heating element 40, a heat sink 50, and an arm assembly 30;

[0044] One end of the boom assembly 30 is connected to the housing 10, and the other end of the boom assembly 30 is provided with a propeller 20.

[0045] The housing 10 has a receiving chamber 12, and the heat sink 50 and the heat generation component 40 are located in the receiving chamber 12. The heat sink 50 is close to or in contact with the heat generation component 40.

[0046] One end of the arm assembly 30 is provided with an air inlet channel 301. The air inlet port of the air inlet channel 301 is located below the propeller 20 and within the rotation area 201 of the propeller 20. The air outlet port of the air inlet channel 301 is connected to the receiving chamber 12, and the receiving chamber 12 is provided with an air outlet 122.

[0047] In this embodiment, the housing 10 is used to mount the arm assembly 30, the heating element 40, and the heat sink 50, and houses the heating element 40 and the heat sink 50 through the receiving chamber 12. One end of the arm assembly 30 is connected to the housing 10, and the other end of the arm assembly 30 is connected to the propeller 20. The heating element 40 is used to cooperate with the propeller 20 to realize the basic functions of the UAV 100. The airflow generated by the propeller 20 enters the receiving chamber 12 through the air inlet port of the air inlet channel 301 and flows out from the air outlet 122, thereby dissipating heat from the heating element 40. The heat sink 50 can improve the heat dissipation efficiency of the heating element 40. By opening an air intake channel 301 at one end of the arm assembly 30, and with the air intake port of the air intake channel 301 located below the propeller 20 and within the rotation area 201 of the propeller 20, when the propeller 20 rotates, the rotation area 201 of the propeller 20 will not overlap with the casing 10, thus preventing the wasted lift of the propeller 20 and improving the flight efficiency and endurance of the UAV 100.

[0048] In some specific embodiments, the heat-generating component 40 includes a motherboard and electronic components. The electronic components are mounted on the motherboard and can be close to or in direct contact with the heat sink 50. When there is a gap between the electronic components and the heat sink 50, thermal grease can be filled into the gap to improve the thermal conductivity between the electronic components and the heat sink 50, thereby improving the heat dissipation efficiency of the electronic components. The heat sink 50 can be made of materials such as aluminum alloy or magnesium alloy. It is understood that, according to user needs, other structural components, such as controllers, batteries, drive motors, etc., can also be set in the housing 10, which will not be exhaustively listed here. One end of the arm assembly 30 can be fixedly or hinged to the side of the housing 10. The drive motor of the propeller 20 can be set at the other end of the arm assembly 30. The drive motor can be electrically connected to the motherboard, which can be a printed circuit board. When the UAV 100 is flying normally, the rotation area 201 of the propeller 20 is slightly larger than the vertical projection area of ​​the rotation radius of the propeller 20.

[0049] In some embodiments, the air inlet port of the air inlet channel 301 is located at the edge of the rotation area 201 of the propeller 20.

[0050] In this embodiment, when the air inlet port of the air inlet channel 301 is located at the edge of the rotation area 201 of the propeller 20, the length of the arm assembly 30 can be reduced as much as possible, and the rotation area 201 of the propeller 20 can be ensured not to overlap with the housing 10, and the airflow generated by the propeller 20 can enter the interior of the receiving chamber 12 from the air inlet port of the air inlet channel 301.

[0051] In some specific embodiments, when the UAV 100 is flying normally, if the vertical projection area of ​​the rotation radius of the propeller 20 is 5cm, the radius of the rotation area 201 can be 5.1cm. The vertical distance between the air inlet port of the air inlet channel 301 and the center line of the rotation area 201 can be 4.9cm, 5.0cm, or 5.1cm.

[0052] In some embodiments, the air inlet of the air inlet channel 301 is located on the top surface of one end of the arm assembly 30, and the other end of the arm assembly 30 is inclined downward.

[0053] In this embodiment, when the air inlet port of the air inlet channel 301 is located on the top surface of the arm assembly 30, the air inlet port of the air inlet channel 301 can face the propeller 20, so that the airflow generated by the propeller 20 can enter from the air inlet port of the air inlet channel 301. The other end of the arm assembly 30 is tilted downwards. When the UAV 100 is flying normally, the height of the other end of the arm assembly 30 is slightly lower than the height of the first end of the arm assembly 30, so that the airflow generated by the propeller 20 can enter more smoothly from the air inlet port of the air inlet channel 301.

[0054] Please refer to the above as well. Figures 4 to 7 ,exist Figure 7 In the diagram, the arrows indicate the direction of airflow. In some embodiments, the arm assembly 30 includes a hinge 60, and the receiving chamber 12 is further provided with a connecting through hole 124. One end of the arm assembly 30 is connected to the hinge 60, which is rotatably mounted on the housing 10 and passes through the connecting through hole 124.

[0055] An air inlet channel 301 is provided inside the hinge 60.

[0056] In this embodiment, the connecting through hole 124 is used to accommodate and install the hinge 60. One end of the arm assembly 30 is hinged to the housing 10 through the hinge 60, so that the arm assembly 30 and the propeller 20 can be folded and stored.

[0057] In some specific embodiments, the arm assembly 30 includes an arm body and a hinge 60, which can be integrally formed with the arm body, thereby improving the connection strength between the hinge 60 and the arm body. It is understood that in some specific embodiments, one end of the arm assembly 30 can also be fixedly connected to the housing 10. The hinge 60 is located on the top surface of the arm body.

[0058] In some specific embodiments, the hinge 60 can be cylindrical, and correspondingly, the wall of the connecting through hole 124 can be arc-shaped. With this configuration, when the arm assembly 30 rotates relative to the housing 10, the hinge 60 can rotate smoothly in the connecting through hole 124. When the arm assembly 30 rotates from the unfolded position to the folded position, the circular hinge 60 can avoid interference with the heat sink 50.

[0059] In some specific embodiments, the drone 100 also includes a hinge shaft 70, which is installed in the connecting through hole 124. The hinge member 60 has a hinge hole, and the hinge shaft 70 passes through the hinge hole so that the hinge member 60 is rotatably connected to the hinge shaft 70.

[0060] In some specific embodiments, the hinge hole can be omitted, and the hinge shaft 70 and the hinge member 60 can be integrally formed, which can improve the connection strength between the hinge shaft 70 and the hinge member 60.

[0061] In some embodiments, the hinge 60 has an inclined surface 62 at one end near the propeller 20. The inclined surface 62 faces the propeller 20 and forms a preset angle with the plane of rotation of the propeller 20. The air inlet port of the air inlet channel 301 passes through the inclined surface 62.

[0062] In this embodiment, by setting an inclined surface 62 and making the air inlet port of the air inlet channel 301 pass through the inclined surface 62, the opening area of ​​the air inlet port of the air inlet channel 301 can be increased, thereby increasing the air intake of the air inlet channel 301 and thus improving the heat dissipation efficiency of the heat-generating component 40.

[0063] In some specific embodiments, when the UAV 100 is flying horizontally, the rotation plane of the propeller 20 is parallel to the horizontal plane, and the preset angle between the tilting surface 62 and the rotation plane can be 30°.

[0064] In some embodiments, the heat sink 50 includes a heat sink substrate 52 and an air guide 54. The heat sink substrate 52 is disposed in the receiving chamber 12. One side of the heat sink substrate 52 faces the heat-generating component 40. The air guide 54 is disposed on the other side of the heat sink substrate 52 and is located at one end of the heat sink substrate 52. The other end of the heat sink substrate 52 extends toward the air outlet 122.

[0065] An air guide 54 has an air passage 542 inside, and the air outlet of the air inlet 301 is connected to the air passage 542.

[0066] In this embodiment, the heat generated by the heat-generating element 40 is transferred to one side of the heat dissipation substrate 52. The heat-generating element 40 is located at one end of the heat dissipation substrate 52, and the other end of the heat dissipation substrate 52 extends toward the air outlet 122, which can increase the heat dissipation area of ​​the heat dissipation substrate 52 and thus improve the heat dissipation efficiency. After part of the airflow generated by the propeller 20 enters through the air inlet port of the air inlet channel 301, it can enter the air passage 542 through the air outlet port of the air inlet channel 301, and be guided to the heat dissipation substrate 52 through the air passage 542, thereby further improving the heat dissipation efficiency of the heat dissipation substrate 52 for the heat-generating element 40.

[0067] In some preferred embodiments, when the arm assembly 30 is in the deployed state, after the air guide 54 and the hinge 60 are connected, there is a small gap between the air outlet of the air inlet channel 301 and the air inlet of the air passage 542, so as to avoid interference between the hinge 60 and the air guide 54.

[0068] Alternatively, in other embodiments, the arm assembly 30 may also be rigidly connected to the housing 10 (i.e., the arm assembly 30 cannot rotate relative to the housing 10). In this case, there is no gap between the air outlet of the air inlet channel 301 and the air inlet of the air passage 542, thus ensuring heat dissipation efficiency.

[0069] In some specific embodiments, reinforcing ribs 522 are provided at the edges of the heat dissipation substrate 52. By providing reinforcing ribs 522, the strength of the heat dissipation substrate 52 can be improved, and the reinforcing ribs 522 can also increase the heat dissipation area. The air guide 54 is in the shape of a fan shroud. When the arm assembly 30 is deployed, the air outlet of the air inlet channel 301 and the air inlet of the air outlet channel 542 are connected. The air guide 54 and the heat dissipation substrate 52 can be integrally formed, which can improve the connection strength between the air guide 54 and the heat dissipation substrate 52, and can reduce processing steps and improve processing efficiency.

[0070] In some specific embodiments, the heat dissipation substrate 52 is connected to the inner wall of the housing 10 by screws or other means.

[0071] In some embodiments, the heat sink 50 further includes a supporting heat sink 56, which is disposed in the air passage 542 and is arranged along the airflow direction of the air passage 542.

[0072] In this embodiment, the supporting heat sink 56 is arranged along the airflow direction of the air passage 542, that is, one end of the supporting heat sink 56 is located near the air inlet port of the air passage 542, and the other end of the supporting heat sink 56 is located near the air outlet port of the air passage 542. The supporting heat sink 56 can divide the air passage 542 into multiple airflow channels, and the air inlet port of each airflow channel is connected to the air outlet port of the air inlet channel 301. The air outlet port of each airflow channel faces the other end of the heat dissipation substrate 52. By setting the supporting heat sink 56, the heat dissipation area can be increased, and it also provides support for the air guide 54, thereby improving the overall strength of the air guide 54.

[0073] In some specific embodiments, the supporting heat sink 56, the air guide 54 and the heat dissipation substrate 52 can be integrally formed, which can improve the connection strength, reduce the number of processing steps and improve the processing efficiency.

[0074] It is understood that in some embodiments, the supporting heat sink 56 may be omitted.

[0075] In some embodiments, the heat sink 50 further includes heat sink fins 58, which are disposed on the other side of the heat sink substrate 52. One end of the heat sink fins 58 is disposed near the air outlet of the air passage 542, and the other end of the heat sink fins 58 extends toward the air outlet 122.

[0076] In this embodiment, by setting heat dissipation fins 58, the heat dissipation area can be increased, and the heat dissipation efficiency can be further improved. Furthermore, one end of the heat dissipation fins 58 is positioned close to the air outlet of the air passage 542, and the other end of the heat dissipation fins 58 is positioned towards the air outlet 122. Therefore, the arrangement direction of the heat dissipation fins 58 is the same as the airflow direction, thus the heat dissipation fins 58 can guide the airflow, making the airflow smoother.

[0077] In some specific embodiments, the supporting heat sink 56, air guide 54, heat dissipation fins 58 and heat dissipation substrate 52 can be integrally formed, which can improve the connection strength, reduce processing steps and improve processing efficiency.

[0078] In some embodiments, there are two air guides 54, and each air guide 54 is provided with an air passage 542.

[0079] The extended lines of the air outlets of the two air passages 542 intersect;

[0080] The heat sink 50 also includes a guide vane 59, which is located on the other side of the heat sink substrate 52 and between the air outlet ports of the two air passages 542.

[0081] In this embodiment, by providing two air guides 54, some of the airflow generated by the propeller 20 can flow into the receiving chamber 12 from multiple directions. This reduces the adverse effects of blocked airflow on the heat dissipation substrate 52 and heat dissipation fins 58, thus improving heat dissipation. The air guide 59 ensures that the airflow does not interfere with each other when passing through the outlet ports of the two air passages 542. Furthermore, the air guide 59 increases the heat dissipation area.

[0082] In some specific embodiments, the two air guides 54 are located on opposite sides of the housing 10. The air inlet ports of the air inlet channels 301 in the two air guides 54 can be connected to the air outlet ports of the same air inlet channel 301. In some other embodiments, the air inlet ports of the air inlet channels 301 in the two air guides 54 can each be connected to the air outlet port of an air inlet channel 301.

[0083] In some specific embodiments, taking the normal flight of the UAV 100 as a reference, the heat-generating component 40 is located below the heat dissipation substrate 52, and the air guide 54, heat dissipation fins 58, air guide 59 and supporting heat dissipation fins 56 are all located on the top surface of the heat dissipation substrate 52.

[0084] In some specific embodiments, the supporting heat sink 56, air guide 54, heat dissipation fins 58, airflow guide 59 and heat dissipation substrate 52 can be integrally formed, which can improve the connection strength, reduce processing steps and improve processing efficiency.

[0085] In some embodiments, the arm assembly 30 includes two first arm assemblies 32, the propeller 20 includes two first propellers 22, and the number of hinges 60 is two.

[0086] Each first arm assembly 32 is connected to a hinge 60 at one end. The two hinges 60 are rotatably mounted on opposite sides of the housing 10 and located at one end of the housing 10. Each hinge 60 is provided with an air inlet channel 301. The air outlet of each air inlet channel 301 is connected to the air inlet port of a corresponding air passage 542. The other end of each first arm assembly 32 is provided with a first propeller 22.

[0087] The number of heat dissipation fins 58 is at least two, and an air guide channel 582 is formed between any two adjacent heat dissipation fins 58. The air inlet of the air guide channel 582 is set close to the air outlet of each air passage 542, and the air outlet of the air guide channel 582 extends toward the air outlet 122.

[0088] In this embodiment, by providing two first arm assemblies 32, two first propellers 22 can be installed. Each first propeller 22 is hinged to the side of the housing 10 via a hinge 60. By providing two first propellers 22, the flight efficiency of the UAV 100 can be improved. By providing multiple heat dissipation fins 58, the heat dissipation area can be increased, improving heat dissipation efficiency. Furthermore, an air guide channel 582 is formed between any two adjacent heat dissipation fins 58. This air guide channel 582 guides the airflow, making the airflow distribution more uniform and ensuring sufficient contact between the airflow and the heat dissipation fins 58, heat dissipation substrate 52, etc., thereby improving heat dissipation efficiency.

[0089] In some specific embodiments, there are four heat dissipation fins 58, with two heat dissipation fins 58 located on one side of the air guide 59 and the other two heat dissipation fins 58 located on the other side of the air guide 59. The four heat dissipation fins 58 form three air guide channels 582. The air inlets of the two outer air guide channels 582 face the air outlet of an air passage 542, respectively. The air guide 59 is located at the front section of the middle air guide channel 582 and divides the front section of the air guide channel 582 into two channels.

[0090] In some specific embodiments, the air inlet port of the air passage 542 in each air guide 54 is connected to the air outlet port of the air inlet passage 301 of a hinge 60. This enables air to enter from both sides of the housing 10, further improving the heat dissipation efficiency of the heat-generating component 40 and enhancing its resistance to unexpected events. Each hinge 60 is located on the top surface of one end of a first arm assembly 32.

[0091] In some embodiments, the arm assembly 30 further includes two second arm assemblies 34, and the propeller 20 further includes two second propellers 24;

[0092] One end of each of the two second arm assemblies 34 is hinged to the opposite sides of the housing 10 and located at the other end of the housing 10. The other end of each second arm assembly 34 is provided with a second propeller 24.

[0093] The air outlet 122 is located at the other end of the housing 10 and between the two second propellers 24.

[0094] In this embodiment, by setting two second arm assemblies 34, two second propellers 24 can be installed. The two first propellers 22 and the two second propellers 24 can improve the lift of the UAV 100. Since the two first propellers 22 are located on both sides of one end of the housing 10 and the two second propellers 24 are located on both sides of the other end of the housing 10, the UAV 100 is more stable during flight. Since the air inlet duct 301, the air outlet 542, etc. are located at one end of the housing 10 and the air outlet 122 is located at the other end of the housing 10, the heat dissipation path can be increased, thereby increasing the heat dissipation area and improving the heat dissipation efficiency. When the UAV 100 is flying forward normally, the first propellers 22 can be located in front of the second propellers 24 and the air outlet 122 is located between the two second propellers 24, so it will not affect the two second propellers 24. Moreover, the airflow from the air outlet 122 can also generate forward thrust for the UAV 100, which can further improve flight efficiency and increase endurance.

[0095] In some specific embodiments, taking the UAV 100 in normal forward flight as a reference, the hinge 60, the first arm assembly 32, and the first propeller 22 are located at the front end of the housing 10. The second arm assembly 34, the second propeller 24, and the air outlet 122 are located at the rear end of the housing 10. That is, the first arm assembly 32 is the forearm, the second arm assembly 34 is the rear arm, the first propeller 22 is the front propeller 20, and the second propeller 24 is the rear propeller 20. It can be understood that, alternatively, the hinge 60, the first arm assembly 32, and the first propeller 22 can be located at the rear end of the housing 10, and the second arm assembly 34, the second propeller 24, and the air outlet 122 can be located at the front end of the housing 10. That is, the first arm assembly 32 is the rear arm, the second arm assembly 34 is the forearm, the first propeller 22 is the rear propeller 20, and the second propeller 24 is the front propeller 20. The air outlet 122 can also be located on the side of the housing 10.

[0096] In some specific embodiments, it is understood that the second arm assembly 34 and the second propeller 24 may be omitted. It is also understood that the number of the first arm assembly 32, the second arm assembly 34, the first propeller 22, and the second propeller 24 may be one, three, or other quantities, which can be reasonably set by the user as needed.

[0097] In some specific embodiments, one end of the second arm assembly 34 can also be fixedly connected to both sides of the housing 10 and located at the other end of the housing 10. The air outlet 122 can be a strip-shaped opening for easy processing. It is understood that the air outlet 122 can also be other shapes.

[0098] An embodiment of the present invention also provides a flight system, which includes a drone 100 and a remote controller. The remote controller is communicatively connected to the drone and can control the flight operations of the drone 100.

[0099] The flight system in this embodiment also has the advantages mentioned above, which will not be repeated here.

[0100] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; under the concept of the present invention, the technical features of the above embodiments or different embodiments can also be combined, the steps can be implemented in any order, and there are many other variations of different aspects of the present invention as described above, which are not provided in detail for the sake of brevity; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A drone, characterized in that, This includes the fuselage, propeller, heat-generating components, heat dissipation components, and arm assembly; One end of the boom assembly is connected to the housing, and the other end of the boom assembly is provided with the propeller; The housing has a receiving chamber, and the heat dissipation component and the heat generation component are disposed in the receiving chamber, with the heat dissipation component close to or in contact with the heat generation component; One end of the arm assembly is provided with an air inlet channel, the air inlet port of the air inlet channel is located below the propeller and within the rotation area of ​​the propeller; the air outlet port of the air inlet channel is connected to the receiving chamber, and the receiving chamber is provided with an air outlet; The arm assembly includes a hinge, and the receiving chamber is also provided with a connecting through hole. One end of the arm assembly is connected to the hinge, and the hinge is rotatably mounted on the housing and passes through the connecting through hole. The air inlet channel is provided inside the hinge; The heat dissipation component includes a heat dissipation substrate and an air guide. The air guide is in the shape of a hood. The heat dissipation substrate is disposed in the receiving cavity. One side of the heat dissipation substrate faces the heat-generating component. The air guide is disposed on the other side of the heat dissipation substrate and is located at one end of the heat dissipation substrate. The other end of the heat dissipation substrate extends toward the air outlet. The air guide has an air passage, and the air outlet of the air inlet channel is connected to the air passage. Part of the airflow generated by the propeller can enter the air passage from the air inlet channel and be guided to the heat dissipation substrate through the air passage. The air inlet of the air inlet channel is located on the top surface of one end of the boom assembly, and the other end of the boom assembly is inclined downwards; The hinge has an inclined surface at one end near the propeller, the inclined surface faces the propeller and forms a preset angle with the plane of rotation of the propeller, and the air inlet port of the air inlet channel passes through the inclined surface.

2. The UAV according to claim 1, characterized in that, The heat dissipation component also includes a supporting heat sink, which is disposed within the air passage and is arranged along the airflow direction of the air passage.

3. The UAV according to claim 1, characterized in that, The heat sink also includes heat sink fins, which are disposed on the other side of the heat sink substrate. One end of the heat sink fins is located near the air outlet of the air passage, and the other end of the heat sink fins extends toward the air outlet.

4. The UAV according to claim 3, characterized in that, The number of air guides is two, and each air guide is provided with the air passage; The extension lines of the air outlet ports of the two air passages intersect; The heat dissipation component also includes a guide vane, which is disposed on the other side of the heat dissipation substrate and located between the air outlet ports of the two air passages.

5. The UAV according to claim 4, characterized in that, The arm assembly includes two first arm assemblies, the propeller includes two first propellers, and the number of the hinges is two. One end of each first arm assembly is connected to a hinge, and the two hinges are respectively rotatably disposed on opposite sides of the housing and located at one end of the housing. Each hinge is provided with an air inlet channel, and the air outlet of each air inlet channel is connected to the air inlet port of a corresponding air passage. The other end of each first arm assembly is provided with a first propeller. The number of heat dissipation fins is at least two, and an air guide channel is formed between any two adjacent heat dissipation fins. The air inlet of the air guide channel is located close to the air outlet of each air passage, and the air outlet of the air guide channel extends toward the air outlet.

6. The UAV according to claim 5, characterized in that, The arm assembly also includes two second arm assemblies, and the propeller also includes two second propellers; One end of each of the two second arm assemblies is hinged to opposite sides of the housing and located at the other end of the housing; the other end of each second arm assembly is provided with a second propeller. The air outlet is located at the other end of the housing and between the two second propellers.

7. A flight system, characterized in that, The flight system includes a drone as described in any one of claims 1-6 and a remote controller, wherein the remote controller is communicatively connected to the drone.

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