Charging device for a drone and drone

Abstract

The application provides a charging device for a UAV and the UAV, and the charging device comprises a base, the base comprises a bearing part and a power supply part, the bearing part is used for bearing the UAV, the bearing part has a plurality of outer edges, the power supply part is arranged at a part of the bearing part and corresponds to the outer edges of the part of the bearing part, and the outer edges of the other part of the bearing part are open; and a power supply assembly is arranged at the power supply part, the power supply assembly comprises a first positive electrode and a first negative electrode, and the power supply assembly is used for charging the UAV. The charging device for the UAV of the application not only facilitates stable landing of the UAV, but also can charge the UAV.

Description

Technical Field

[0001] This invention relates to the field of drone technology, and more specifically, to a charging device for drones and a drone. Background Technology

[0002] Existing aircraft chargers are bowl-shaped structures, open at the top and closed on all sides. When the aircraft descends, the downdraft easily creates turbulence when encountering this structure, making landing difficult. Furthermore, the common bowl-shaped structure tends to result in poor landing accuracy, with a significant chance that the aircraft will not land precisely within it. In addition, existing bowl-shaped chargers have low heat dissipation efficiency. Summary of the Invention

[0003] This invention provides a new technical solution for a charging device for drones, which can at least solve the problems of bowl-shaped chargers in the prior art, such as being detrimental to aircraft landing and having low heat dissipation efficiency.

[0004] The present invention also provides a drone that can be used with the charging device provided by the present invention.

[0005] According to a first aspect of the present invention, a charging device for a drone includes: a base, the base including a support portion and a power supply portion, the support portion being used to support the drone, the support portion having a plurality of outer edges, the power supply portion being disposed on a portion of the support portion and corresponding to the outer edge of the portion of the support portion, the outer edges of other portions of the support portion being open; and a power supply assembly disposed on the power supply portion, the power supply assembly including a first positive electrode and a first negative electrode, the power supply assembly being used to charge the drone.

[0006] Optionally, the power supply unit is located on one side of the support unit, and the power supply unit cooperates with the support unit to form an opening.

[0007] Optionally, the supporting part has a supporting surface for supporting the UAV, and the power supply part has a power supply surface on which the first positive electrode and the first negative electrode are installed, and the power supply surface and the supporting surface cooperate to form an opening.

[0008] Optionally, the plurality of outer edges of the support portion include a first outer edge and a second outer edge that are joined together. The support portion is joined to the power supply portion through the first outer edge. The power supply portion extends along a first direction, the first outer edge extends along a second direction, and the second outer edge extends along a third direction. The first positive electrode and the first negative electrode are spaced apart along the first direction, and / or at least one of the first positive electrode and the first negative electrode is an elongated strip that extends along the second direction.

[0009] Optionally, the charging device for the drone further includes a heat sink connected to the base and capable of heat exchange with the base.

[0010] According to a second aspect of the present invention, a drone is provided for use with a charging device having an open structure. The charging device includes a base and a power supply assembly. The base includes a support portion and a power supply portion. The power supply portion is disposed on a portion of the support portion and corresponds to the outer edge of the portion of the support portion. The outer edges of other portions of the support portion are open. The power supply assembly is disposed on the power supply portion and includes a first positive electrode and a first negative electrode. The drone includes: a fuselage, an energy storage device installed within the fuselage, the energy storage device having at least one electrode pair, the electrode pair including a second positive electrode and a second negative electrode, an outer surface of the fuselage including a charging surface and a landing surface, the electrode pair being mounted on the charging surface and positioned with the power supply assembly, the landing surface corresponding to the support portion; and a rotor mounted on the fuselage.

[0011] Optionally, the outer surface of the fuselage includes a bottom surface, an end surface, and multiple side surfaces, the multiple side surfaces being located between the end surface and the bottom surface, the bottom surface being formed as the landing surface, at least one of the side surfaces being formed as the charging surface, and the rotor being mounted on the end surface.

[0012] Optionally, the second positive electrode and the second negative electrode are spaced apart along the direction from the end face to the bottom surface, and / or, at least one of the second positive electrode and the second negative electrode is an elongated strip extending along the extension direction of the side face that contacts the bottom surface.

[0013] Optionally, the area of ​​the first positive electrode is larger than the area of ​​the second positive electrode, and / or the area of ​​the first negative electrode is larger than the area of ​​the second negative electrode.

[0014] Optionally, the drone further includes a metal component and a magnetic component, one of which is mounted on the fuselage and the other is mounted on the base, wherein the magnetic component is capable of attracting the metal component.

[0015] The charging device for drones according to embodiments of the present invention adopts an open structure, eliminating the need for a closed structure on all sides. This prevents turbulence in the downdraft during drone descent, resulting in a more stable landing. Furthermore, the open structure of the drone charging device of the present invention facilitates heat dissipation and prevents heat accumulation.

[0016] Other features and advantages of the invention will become clear from the following detailed description of exemplary embodiments of the invention with reference to the accompanying drawings. Attached Figure Description

[0017] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments of the invention and, together with their description, serve to explain the principles of the invention.

[0018] Figure 1 This is a schematic diagram of an unmanned aerial vehicle (UAV) system according to an embodiment of the present invention;

[0019] Figure 2 This is a perspective view of a charging device for a drone according to an embodiment of the present invention;

[0020] Figure 3 This is a schematic diagram of the internal structure of a charging device for a drone according to an embodiment of the present invention;

[0021] Figure 4 This is a schematic diagram of the structure of a drone according to an embodiment of the present invention.

[0022] Figure Labels

[0023] Charging device 100;

[0024] Base 10; Supporting part 11; Supporting surface 111; Power supply part 12; Power supply surface 121; Through hole 112;

[0025] Power supply component 20; First positive terminal 21; First negative terminal 22;

[0026] Magnetic attachment 30;

[0027] Radiator 40;

[0028] 200 UAV; 201 fuselage; 202 end face; 203 side; 204 rotor; 205 second positive electrode; 206 second negative electrode; 207 metal part. Detailed Implementation

[0029] Various exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It should be noted that, unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention.

[0030] The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the invention or its application or use.

[0031] Techniques, methods, and equipment known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and equipment should be considered part of the specification.

[0032] In all the examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values.

[0033] It should be noted that similar labels and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be discussed further in subsequent figures.

[0034] The charging device 100 for a drone according to an embodiment of the present invention will now be described in detail with reference to the accompanying drawings.

[0035] like Figures 1 to 4 As shown, a charging device 100 for a drone 200 according to an embodiment of the present invention includes a base 10 and a power supply component 20.

[0036] Specifically, the base 10 includes a support portion 11 and a power supply portion 12. The support portion 11 is used to support the drone 200 and has multiple outer edges. The power supply portion 12 is located on a part of the support portion 11 and corresponds to the outer edge of a part of the support portion 11. The outer edges of other parts of the support portion 11 are open. The power supply component 20 is located on the power supply portion 12 and includes a first positive electrode 21 and a first negative electrode 22. The power supply component 20 is used to charge the drone 200.

[0037] In other words, the base 10 mainly consists of a support part 11 and a power supply part 12. Optionally, the base 10 is a one-piece molded part, which facilitates processing and production. The support part 11 can be used to support the landing drone 200 and provide support for the drone 200. A power supply component 20 is installed on the power supply part 12. The power supply component 20 includes a first positive electrode 21 and a first negative electrode 22. The power supply component 20 can charge the drone 200 that lands on the support part 11. That is, the power supply component 20 installed on the power supply part 12 can charge the charging structure of the drone 200. The drone 200 may include a second positive electrode 205 and a second negative electrode 206. The first positive electrode 21 and the first negative electrode 22 of the power supply component 20 can be hidden inside the base 10 to realize wireless charging function, or they can be exposed on the power supply surface 121 and contact the second positive electrode 205 and the second negative electrode 206 of the charging structure for charging. That is to say, in this embodiment, the charging method and the specific form of the power supply component 20 are not limited.

[0038] It should be noted that the power supply unit 12 is located on a portion of the support portion 11 and corresponds to the outer edge of that portion of the support portion 11. The outer edges of other portions of the support portion 11 are open. In other words, in this embodiment, except for the area where the power supply unit 12 is located, the other areas of the support portion 11 are open areas. That is, the support portion 11 has a large range of open sides, allowing the drone 200 to land from multiple directions during its descent towards the support portion 11, thus avoiding interference to the drone 200. After landing on the support portion 11, the drone 200 can be powered by the power supply component 20 on the charging unit 12.

[0039] Furthermore, existing aircraft chargers are bowl-shaped structures that are open at the top and closed on all sides. When the aircraft descends, the downward airflow encounters this structure, easily creating turbulence and making landing difficult. Moreover, the common bowl-shaped structure tends to result in poor landing accuracy, with a significant probability that the aircraft will not land accurately within it. Additionally, existing bowl-shaped chargers have low heat dissipation efficiency.

[0040] In contrast, the charging device 100 of the drone 200 of the present invention adopts an open structure. This open structure has the characteristic of being open with multiple degrees of freedom, eliminating the need for a closed structure on all four sides compared to existing technologies. When the drone 200 descends, the downdraft will not generate turbulence, making the landing more stable. Furthermore, the open structure of the charging device 100 of the drone 200 of the present invention facilitates heat dissipation and prevents heat accumulation.

[0041] According to one embodiment of the present invention, the power supply unit 12 is located on one side of the support unit 11, and the power supply unit 12 and the support unit 11 cooperate to form an opening. That is, by the mutual cooperation of the power supply unit 12 and the support unit 11, the base 10 can be realized as an open structure with an opening. For example, the support unit 11 is a rectangular piece with four outer edges, the power supply unit 12 is disposed on the support unit 11 and close to one outer edge, and the power supply unit 12 also protrudes from the support unit 11. The power supply unit 12 and the support unit 11 can cooperate to form an L-shaped base 10, in which case the base 10 has an opening, and the drone 200 can be parked at the opening position. In this embodiment, by defining the mutual positional relationship between the power supply unit 12 and the support unit 11, it is beneficial to position and cooperate the power supply components on the power supply unit 12 with the electrode pairs on the drone 200.

[0042] In some specific embodiments of the present invention, the support part 11 has a support surface 111 for supporting the UAV 200, and the power supply part 12 has a power supply surface 121 on which a first positive electrode 21 and a first negative electrode 22 are installed. The power supply surface 121 and the support surface 111 cooperate to form an opening.

[0043] In other words, the base 10 has a bearing surface 111 and a power supply surface 121. The bearing surface 111 has an open side, and the open portion of the bearing surface 111 can support the UAV 200. The power supply surface 121 can be located on the open side of the bearing surface 111. In addition, other parts of the bearing surface 111 are open, that is, the bearing surface 111 has a large open area. During the descent of the UAV 200 toward the bearing surface 111, the multiple open openings of the bearing surface 111 can prevent the UAV 200 from being interfered with.

[0044] In some specific embodiments of the present invention, the multiple outer edges of the support portion 11 include a first outer edge and a second outer edge that are joined together. The support portion 11 is joined to the power supply portion 12 through the first outer edge. The power supply portion 12 extends along a first direction, the first outer edge extends along a second direction, and the second outer edge extends along a third direction.

[0045] Optionally, any two of the second direction, the first direction, and the third direction have an included angle, which can be an acute angle, a right angle, or an obtuse angle.

[0046] Optionally, any two of the second direction, the first direction, and the third direction are perpendicular to each other. For example, the third direction is the X-axis direction, the second direction is the Y-axis direction, and the first direction is the Z-axis direction.

[0047] In other words, the arrangement of the second direction with a non-0° and non-180° angle to the first direction is beneficial for charging the energy storage device of the drone 200 when it lands on the bearing surface 111, in conjunction with the positions of the second positive electrode 205 and the second negative electrode 206 on the fuselage 201 of the drone 200. It is also beneficial for offsetting the positions of the second positive electrode 205 and the second negative electrode 206 on the fuselage 201 from the bottom surface of the fuselage 201. When the bottom surface of the drone 200 lands and contacts the bearing surface 111, the power supply component 20 on the base 10 can quickly position itself with the second positive electrode 205 and the second negative electrode 206 of the drone 200, thereby achieving rapid charging of the drone 200.

[0048] It should be noted that existing aircraft use bowl-shaped chargers that are open at the top and closed on all sides. During charging, the aircraft descends, and the downward airflow encounters the bowl-shaped charger, causing turbulence and making landing difficult and inaccurate. Furthermore, the bowl-shaped charger has low heat dissipation efficiency. In contrast, the drone 200 of this embodiment can land on the support surface 111 from multiple angles, such as from the top, left, right, or opposite side of the power supply surface 121. It can also fly away from the support surface 111 in multiple directions. During landing or takeoff, because multiple positions on the support surface 111 are open, the downward airflow of the drone 200 will not encounter turbulence structures, thus not affecting the drone 200's flight and landing. Moreover, the increased freedom of movement on the support surface 111 allows the drone 200 to land on the support 11 in multiple directions, reducing landing difficulty and improving landing accuracy. In addition, the side-open design of the support surface 111 improves the heat dissipation efficiency for the drone 200. When the drone 200 lands on the bearing surface 111 for charging, the second positive electrode 205 of the drone 200's electrode pair contacts the first positive electrode 21, and the second negative electrode 206 contacts the second negative electrode 22, thereby enabling the power supply component 20 to charge the drone 200.

[0049] For example, the first direction is vertical, the second direction is forward and backward, and the third direction is left and right. During the descent of the drone 200 towards the support surface 111, the reduced presence of obstacles above the support surface 111 prevents interference with the drone 200's descent. Furthermore, since the power supply surface 121 extends vertically, after the drone 200 lands on the support surface 111, its fuselage 201 can be positioned opposite the power supply surface 121, facilitating the rapid establishment of electrical connections between the power supply component 20 and the drone 200's second positive terminal 205 and second negative terminal 206.

[0050] According to one embodiment of the present invention, the first positive electrode 21 and the first negative electrode 22 are distributed approximately spaced apart along a first direction, for example, the first positive electrode 21 and the first negative electrode 22 are distributed approximately spaced apart along a vertical direction, which facilitates rapid positioning with the second positive electrode 205 and the second negative electrode 206 of the landing UAV 200, and avoids the need for the UAV 200 to be repositioned in the first direction.

[0051] In some specific embodiments of the present invention, at least one of the first positive electrode 21 and the first negative electrode 22 is elongated and extends generally along a second direction, for example, a horizontal direction. When the UAV 200 lands on the bearing surface 111, the first positive electrode 21 or the second negative electrode 22 extends horizontally, which facilitates quick positioning with the second positive electrode 205 and the second negative electrode 206 of the landed UAV 200, avoiding the need for repositioning of the UAV 200 in the second direction.

[0052] According to one embodiment of the present invention, such as Figure 2 and Figure 3 As shown, the charging device 100 for the drone 200 also includes a heat sink 40, which is connected to the base 10 and can exchange heat with the base 10. That is, the heat sink 40 can control the temperature of the base 10. For example, by controlling the temperature near the power supply surface 121, it is beneficial to control the temperature of the power supply component 20; by controlling the temperature near the load 111, it is beneficial to control the temperature of the drone 200.

[0053] In other words, the base 10 of this invention adopts an open structure, allowing for effective heat transfer. Furthermore, by incorporating a heat sink 40, effective heat dissipation can be further achieved. Specifically, this heat sink can dissipate heat from the drone 200 during charging, preventing excessive heat buildup during charging.

[0054] In some specific embodiments of the present invention, such as Figure 2 and Figure 3 As shown, the base 10 defines a receiving space, and the heat sink 40 is installed in the receiving space. The base 10 has a through hole 112 along its wall thickness direction. The first end of the through hole 112 penetrates the bearing surface 111, and the second end of the through hole 112 communicates with the receiving space. That is, the heat sink 40 can exchange heat with the drone 200 that lands on the bearing surface 111 through the through hole 112. For example, it can dissipate heat from the energy storage device inside the fuselage 201 of the drone 200, which is beneficial for achieving fast charging.

[0055] Optionally, the heat sink 40 is a fan, and the airflow generated by the fan can pass through the through hole 112 to cool the drone 200.

[0056] The present invention also provides a drone 200 for use with a charging device 100 having an open structure. The charging device 100 includes a base 10 and a power supply component 20. The base 10 includes a support portion 11 and a power supply portion 12. The power supply portion 12 is disposed on the outer edge of a portion of the support portion 11, and the outer edges of other portions of the support portion 11 are open. The power supply component 20 is disposed on the power supply portion 12 and includes a first positive electrode 21 and a first negative electrode 22. The drone 200 includes a fuselage 201 and a rotor 204. An energy storage device is installed inside the fuselage 201. The energy storage device has at least one electrode pair, which includes a second positive electrode 205 and a second negative electrode 206. The outer surface of the fuselage 201 includes a charging surface and a landing surface. The electrode pair is mounted on the charging surface and positioned with the power supply component 20. The landing surface corresponds to the support portion 11. The rotor 204 is mounted on the fuselage 201.

[0057] In other words, the present invention also provides a drone 200, such as Figure 1 As shown, the drone 200 includes a fuselage 201 and a rotor 204 mounted on the fuselage 201. An energy storage device is installed inside the fuselage 201, and the energy storage device has a second positive electrode 205 and a second negative electrode 206. It should be noted that since the outer surface of the fuselage 201 includes a charging surface and a landing surface, and the electrode pair is mounted on the charging surface, when the drone 200 lands on the charging device 100, the electrode pair is positioned with the power supply component 20. At this time, the second positive electrode 205 corresponds to the first positive electrode 21, and the second negative electrode 206 corresponds to the first negative electrode 22 to charge the energy storage device. Furthermore, the landing surface corresponds to the support portion 11. Therefore, the charging device 100 for the drone 200 of any of the above embodiments can be used to charge the drone 200.

[0058] In other words, the charging structure of the drone 200 is set on the fuselage 201. When the drone 200 lands on the bearing surface 111, the charging structure of the drone 200 can be paired and positioned with the power supply component 20 of the charging device 100, so as to achieve the rapid and stable landing of the drone 200 while charging the drone 200.

[0059] According to one embodiment of the present invention, the outer surface of the fuselage 201 includes a bottom surface, an end surface 202 and a plurality of side surfaces 203, the plurality of side surfaces 203 being located between the end surface 202 and the bottom surface, the bottom surface being formed as a landing surface, at least one side surface 203 being formed as a charging surface, and the rotor 204 being mounted on the end surface 202.

[0060] In other words, the outer surface of the fuselage 201 includes a bottom surface, an end surface 202, and multiple side surfaces 203. The multiple side surfaces 203 are located between the end surface 202 and the bottom surface. The end surface 202 is connected to the rotor 204, and the bottom surface is supported by the bearing surface 111. At least one side surface 203 is provided with a second positive electrode 205 and a second negative electrode 206. For example, the fuselage 201 is a rectangular component with four side surfaces 203. A second positive electrode 205 and a second negative electrode 206 can be provided on multiple side surfaces 203, or even on each side surface 203. This allows any side surface 203 of the UAV 200 to correspond to the power supply surface 121 and to quickly establish an electrical connection with the power supply component 20 when the UAV 200 lands.

[0061] According to one embodiment of the present invention, the second positive electrode 205 and the second negative electrode 206 are spaced apart along the direction from the end face 202 to the bottom surface, and / or, at least one of the second positive electrode 205 and the second negative electrode 206 is an elongated strip extending along the extension direction of the side surface 203 that connects to the bottom surface. For example, the side surface 203 is a rectangular surface extending vertically, the lower edge of the side surface 203 is connected to the bottom surface and extends horizontally, the upper edge of the side surface 203 extends vertically, the second positive electrode 205 and the second negative electrode 206 are spaced apart along the vertical direction, and at least one of the second positive electrode 205 and the second negative electrode 206 is an elongated strip extending along the extension direction of the lower edge of the side surface 203. It can be seen that by defining the second positive electrode 205 and the second negative electrode 206 as spaced apart along the direction from the end face 202 to the bottom surface, it is convenient to quickly position them with the first positive electrode 21 and the first negative electrode 22 of the charging device 100, avoiding the need for vertical repositioning of the drone 200. By defining at least one of the second positive electrode 205 and the second negative electrode 206 as an elongated strip extending along the side 203 that connects to the bottom surface, it is easy to quickly position it with the first positive electrode 21 and the first negative electrode 22 of the charging device 100, thus avoiding the need for the drone 200 to be repositioned in the horizontal direction.

[0062] According to one embodiment of the present invention, such as Figure 1 and Figure 2 As shown, the area of ​​the first positive electrode 21 is larger than the area of ​​the second positive electrode 205, and / or, the area of ​​the first negative electrode 22 is larger than the area of ​​the second negative electrode 206. In this embodiment, by increasing the area of ​​the first positive electrode 21 and / or the first negative electrode 22, the positioning area can be expanded, thereby further improving charging efficiency without requiring long-term adjustments to the position of the drone 200.

[0063] In some specific embodiments of the present invention, such as Figures 1 to 4As shown, the drone 200 also includes a metal part 207 and a magnetic part 30. One of the metal part 207 and the magnetic part 30 is mounted on the fuselage 201, and the other of the metal part 207 and the magnetic part 30 is mounted on the base 10. The magnetic part 30 is able to generate an attractive force on the metal part 207.

[0064] For example, a metal part 207 is installed on the fuselage 201, which can correspond to the position of the magnetic part 30 on the base 10, improving the guiding effect on the drone 200. By using the magnetic part 30 and the metal part 207 in combination, the drone 200 can be attracted when it approaches to a certain distance, enabling accurate landing and facilitating rapid approach to the position of the power supply component 20.

[0065] In this embodiment, the magnetic chuck 30 can guide the drone 200 to land. That is, the magnetic chuck 30 can magnetically attract the metal part 207 of the drone 200 and apply force to the drone 200. By guiding the drone 200 to a preset position, the positioning efficiency of the power supply component 20 and the charging structure of the drone 200 is improved.

[0066] Optionally, such as Figure 1 and Figure 2 As shown, the magnetic suction component 30 and the power supply component 20 are arranged sequentially along the first direction, and their positions can be interchanged. Correspondingly, the metal component 207 and the charging structure of the drone 200 can also be arranged sequentially along the first direction.

[0067] It should be noted that during the landing of the drone 200, the magnetic attachment 30 generates an attractive force on the metal component 207, thereby guiding the drone 200. If the magnetic attachment 30 and the power supply component 20 are arranged along a third or second direction, the fuselage 201 will tend to be larger. For example, the first direction is up and down, the second direction is inward and outward, and the third direction is left and right. If the magnetic attachment 30 and the power supply component 20 are arranged along the inward and outward direction or along the left and right direction, the corresponding fuselage 20 needs to have a larger width to accommodate the metal component 207 and the charging structure arranged along the third or second direction.

[0068] Optionally, the magnetic component 30 is an electromagnet, which facilitates control of opening and closing. For example, when the drone 200 lands, the electromagnet is activated, and the drone 200 can be attracted when it approaches the base 10, avoiding insufficient landing accuracy. After the drone 200 lands on the base 10, the charging structure comes into contact with the power supply component 20, and at the same time, the electromagnet provides a force for the charging structure to make close contact with the power supply component 20. At this time, the charging device 100 charges the drone 200.

[0069] Optionally, a metal part 207 is provided on each side 203, which helps to ensure that charging can be achieved when either side 203 of the drone 200 is positioned opposite the power supply surface 121.

[0070] The present invention also provides an unmanned aerial vehicle (UAV) system, such as Figure 1 As shown, the drone system includes a drone 200 and a charging device 100. The drone 200 can be any of the drones 200 described above, and the charging device 100 for the drone 200 can be any of the charging devices 100 described above. When the drone 200 lands on the support surface 111, the second positive electrode 205 corresponds to the first positive electrode 21, and the second negative electrode 206 corresponds to the first negative electrode 22, to charge the energy storage device.

[0071] In summary, the charging device 100, the drone, and the drone system according to embodiments of the present invention not only facilitate the stable and rapid landing of the drone 200, but also enable the drone 200 to achieve fast charging and efficient heat dissipation.

[0072] While specific embodiments of the invention have been described in detail by way of examples, those skilled in the art should understand that the examples are for illustrative purposes only and not intended to limit the scope of the invention. Those skilled in the art should understand that modifications can be made to the above embodiments without departing from the scope and spirit of the invention. The scope of the invention is defined by the appended claims.

Claims

1. A charging device for unmanned aerial vehicles, characterized in that, include: The base includes a support portion and a power supply portion. The support portion is used to support the drone and has multiple outer edges. The power supply portion is located on a part of the support portion and corresponds to the outer edge of that part of the support portion. The outer edges of other parts of the support portion are open. The power supply portion is located on one side of the support portion and cooperates with the support portion to form an opening. A power supply component is provided in the power supply section. The power supply component includes a first positive terminal and a first negative terminal. The power supply component is used to charge the drone. The drone includes a fuselage, the outer surface of which includes a bottom surface, an end surface and multiple side surfaces. The multiple side surfaces are located between the end surface and the bottom surface. The bottom surface is formed as a landing surface. The rotor is mounted on the end surface. Each side surface is formed as a charging surface. Each side surface is provided with a second positive electrode and a second negative electrode. The first positive electrode and the first negative electrode are spaced apart along a first direction, and at least one of the first positive electrode and the first negative electrode is an elongated strip extending along a second direction. The length of the first positive electrode extending along the second direction is longer than the length of the second positive electrode of the UAV, the length of the first negative electrode extending along the second direction is longer than the length of the second negative electrode of the UAV, and the area of ​​the first positive electrode is larger than the area of ​​the second positive electrode, and / or the area of ​​the first negative electrode is larger than the area of ​​the second negative electrode.

2. The charging device for a drone according to claim 1, wherein the supporting part has a supporting surface for supporting the drone, the power supply part has a power supply surface, the first positive electrode and the first negative electrode are mounted on the power supply surface, and the power supply surface and the supporting surface cooperate to form an opening.

3. The charging device for a drone according to claim 1, characterized in that, The plurality of outer edges of the bearing portion include a first outer edge and a second outer edge that are joined together. The bearing portion is joined to the power supply portion through the first outer edge. The power supply portion extends along a first direction, the first outer edge extends along a second direction, and the second outer edge extends along a third direction.

4. The charging device for a drone according to claim 1, characterized in that, Also includes: A radiator, which is connected to the base and is capable of exchanging heat with the base.

5. A drone, characterized in that, The drone is used to cooperate with a charging device with an open structure. The charging device includes a base and a power supply assembly. The base includes a support portion and a power supply portion. The power supply portion is located on a part of the support portion and corresponds to the outer edge of the part of the support portion. The outer edges of other parts of the support portion are open. The power supply portion is located on one side of the support portion and cooperates with the support portion to form an opening. The power supply component is disposed in the power supply section. The power supply component includes a first positive electrode and a first negative electrode. The first positive electrode and the first negative electrode are spaced apart along a first direction. At least one of the first positive electrode and the first negative electrode is a strip-shaped component that extends along a second direction. The length of the first positive electrode extending along the second direction is longer than the length of the second positive electrode of the UAV. The length of the first negative electrode extending along the second direction is longer than the length of the second negative electrode of the UAV. The area of ​​the first positive electrode is larger than the area of ​​the second positive electrode, and / or the area of ​​the first negative electrode is larger than the area of ​​the second negative electrode. The drone includes: The fuselage has an energy storage device installed inside it. The energy storage device has at least one electrode pair, which includes a second positive electrode and a second negative electrode. The outer surface of the fuselage includes a charging surface and a landing surface. The electrode pair is installed on the charging surface and positioned with the power supply component. The landing surface corresponds to the bearing part. Rotor, the rotor being mounted on the fuselage; The outer surface of the fuselage includes a bottom surface, an end surface, and multiple side surfaces. The multiple side surfaces are located between the end surface and the bottom surface. The bottom surface is formed as the landing surface. The rotor is mounted on the end surface. Each side surface is formed as the charging surface. Each side surface is provided with a second positive electrode and a second negative electrode.

6. The UAV according to claim 5, characterized in that, The second positive electrode and the second negative electrode are spaced apart along the direction from the end face to the bottom surface, and / or, at least one of the second positive electrode and the second negative electrode is an elongated strip extending along the extension direction of the side face that contacts the bottom surface.

7. The UAV according to claim 5, characterized in that, Also includes: A metal part and a magnetic component, one of which is mounted on the body and the other of which is mounted on the base, wherein the magnetic component is capable of attracting the metal part.

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