Support and unmanned aerial vehicle hangar

Abstract

The support is used for storing and / or transporting an unmanned aerial vehicle and comprises a support body and a supporting mechanism, and the support body is provided with a first side and a second side which are opposite in the first direction; the supporting mechanism is connected to the frame body and comprises a first supporting assembly and a second supporting assembly, the first supporting assembly is used for supporting a first unmanned aerial vehicle which penetrates through the frame body from the first side part and extends to the second side, and the second supporting assembly is used for supporting a second unmanned aerial vehicle which penetrates through the frame body from the second side part and extends to the first side; the first supporting assembly and the second supporting assembly enable the first unmanned aerial vehicle and the second unmanned aerial vehicle to be partially staggered in the second direction, and the second direction is perpendicular to the first direction. According to the technical scheme, transportation and / or storage of the unmanned aerial vehicle can be facilitated, and the occupied space of the unmanned aerial vehicle during storage can be saved.

Description

Technical Field

[0001] The present disclosure relates to the technical field of unmanned aerial vehicle (UAV) devices, and more particularly, to a bracket and a UAV hangar. Background Art

[0002] A UAV is an aircraft that is remotely controlled by radio control equipment and a self - contained program control device. A UAV includes a power system, a flight control system, a video system, a remote control system, etc. Among them, the power system mainly includes propellers, motors, and electronic speed controllers integrated on the arms. For the convenience of storage, maintenance, and transportation, the arms and the fuselage are usually installed in a detachable and replaceable form.

[0003] In the related art, when a UAV travels from a hangar to an operation point, it usually relies on manual handling. This method has low handling efficiency, wastes manpower, and has high labor costs. At the same time, during the handling of the UAV, when the UAV is handled and loaded / unloaded, there are situations such as damaged propellers and bumped airframes. When storing the UAV at the operation point, due to the structural characteristics of the UAV, for example, the arms of the UAV extend a relatively long distance outward from the fuselage and the propellers installed on the arms are relatively large in size, and limited by the overall irregular shape of the UAV, the space occupied during storage is relatively large. If the arms and the fuselage of the UAV are disassembled and stored separately, it is easy to cause damage to parts such as propellers, and at the same time, installation is required again during use, resulting in higher costs. Summary of the Invention

[0004] The purpose of the present disclosure is to provide a bracket and a UAV hangar to facilitate the transportation and / or storage of UAVs and save the space occupied during UAV storage, so as to at least partially solve the above - mentioned technical problems.

[0005] To achieve the above purpose, according to the first aspect of the present disclosure, a bracket for storing and / or transporting a UAV is provided. The bracket includes:

[0006] A frame body having a first side and a second side opposite to each other in a first direction; and

[0007] A support mechanism connected to the frame body and including a first support component and a second support component. The first support component is used to support a first UAV that partially passes through the frame body from the first side and extends to the second side, and the second support component is used to support a second UAV that partially passes through the frame body from the second side and extends to the first side. The first support component and the second support component arrange the first UAV and the second UAV in a partially offset manner in a second direction perpendicular to the first direction.

[0008] Optionally, the first support assembly includes a first support portion and a second support portion. The first support portion is located on the first side and is used to support the arm or fuselage of the first drone. The second support portion is located on the second side and is used to support the landing gear of the first drone; and / or,

[0009] The second support assembly includes a third support portion and a fourth support portion. The third support portion is located on the second side and is used to support the arm or fuselage of the second drone. The fourth support portion is located on the first side and is used to support the landing gear of the second drone.

[0010] Optionally, the first support portion and the third support portion are connected by a support beam connected to the frame; and / or,

[0011] The first support portion has a first bearing groove with an upward opening, and the first bearing groove is used to support the arm or fuselage of the first drone; and / or,

[0012] The third support portion has a second bearing groove with an upward opening, and the second bearing groove is used to support the arm or fuselage of the second drone.

[0013] Optionally, the first support assembly further includes a fifth support portion located between the first support portion and the second support portion in the first direction, and the fifth support portion is used to fix the landing gear of the first drone; and / or,

[0014] The second support assembly further includes a sixth support portion located between the third support portion and the fourth support portion in the first direction, and the sixth support portion is used to fix the landing gear of the second drone.

[0015] Optionally, the fifth support portion is rotatably connected to the frame, and the fifth support portion has a first opening groove, and the first opening groove is used to sleeved or disengaged from the leg of the landing gear of the first drone as the fifth support portion rotates, so as to limit the first drone in the third direction; and / or,

[0016] The sixth support portion is rotatably connected to the frame, and the sixth support portion has a second opening groove, and the second opening groove is used to sleeved or disengaged from the leg of the landing gear of the second drone as the sixth support portion rotates, so as to limit the second drone in the third direction.

[0017] Optionally, the frame has a first limiting portion for limiting the rotation angle of the fifth support portion; and / or,

[0018] The frame has a second limiting portion for limiting the rotation angle of the sixth support portion.

[0019] Optionally, the first support part is detachably connected with a first mating part, and the first mating part cooperates with the first support part to clamp the machine arm; and / or,

[0020] The third support part is detachably connected with a second mating part, and the second mating part cooperates with the third support part to clamp the machine arm.

[0021] Optionally, the frame body includes at least two upright columns arranged side by side and spaced apart along the second direction, and each of the upright columns is provided with the support mechanism.

[0022] According to another aspect of the present disclosure, there is provided an unmanned aerial vehicle hangar, including:

[0023] A storage cabinet, the storage cabinet includes a first cabinet body and the above-mentioned bracket, and the bracket is movably connected to the first cabinet body so as to be able to be pulled out from the first cabinet body or stored in the first cabinet body;

[0024] A transfer cabinet, the transfer cabinet includes a second cabinet body, a vehicle body and the above-mentioned bracket arranged on the vehicle body; the second cabinet body has an accommodation space for accommodating the vehicle body and the bracket and a closable opening for the vehicle body and the bracket to enter and exit the accommodation space; and

[0025] A spare parts cabinet for placing spare parts of the unmanned aerial vehicle;

[0026] Wherein, the storage cabinet, the transfer cabinet and the spare parts cabinet are arranged side by side and detachably connected.

[0027] Optionally, a power supply is arranged in the spare parts cabinet, and power supply interfaces connected to the power supply are arranged in the storage cabinet and the transfer cabinet; and / or,

[0028] A wireless communication module is arranged in the spare parts cabinet; and / or,

[0029] A data uploading system is arranged in the spare parts cabinet.

[0030] Through the above technical solutions, the transportation and / or storage of the unmanned aerial vehicle can be made more convenient. For example, the transportation efficiency is high, the storage space occupied is small, and the transportation and / or storage do not require repeated disassembly and assembly of the unmanned aerial vehicle. Specifically, by using the bracket to store at least the first unmanned aerial vehicle and the second unmanned aerial vehicle, the effect of saving space occupancy is particularly obvious. For example, the first unmanned aerial vehicle and the second unmanned aerial vehicle can be respectively placed on the bracket through the first support assembly and the second support assembly. Among them, the first unmanned aerial vehicle and the second unmanned aerial vehicle partially penetrate the frame body in the first direction to achieve storage extending from the first side to the second side or from the second side to the first side. Compared with storing entirely on the first side or the second side, the occupied space in the first direction is reduced. At the same time, the first support assembly and the second support assembly enable the first unmanned aerial vehicle and the second unmanned aerial vehicle to be partially misaligned in the second direction, that is to say, the projections of the first unmanned aerial vehicle and the second unmanned aerial vehicle in the first direction partially overlap. When storing, part of the structure of the first unmanned aerial vehicle is located in the gap between different structures of the second unmanned aerial vehicle, and part of the structure of the second unmanned aerial vehicle is located in the gap between different structures of the first unmanned aerial vehicle. Thus, the gaps between different structures of the first unmanned aerial vehicle and the second unmanned aerial vehicle form a storage space, enabling the first unmanned aerial vehicle and the second unmanned aerial vehicle to be partially misaligned along the second direction to reduce the occupied space in the second direction.

[0031] Other features and advantages of the present disclosure will be described in detail in the subsequent specific implementation section. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The drawings are used to provide a further understanding of the present disclosure and constitute a part of the specification. Together with the following specific implementation, they are used to explain the present disclosure, but do not constitute a limitation to the present disclosure. In the drawings:

[0033] Figure 1 is the overall structural schematic diagram of the unmanned aerial vehicle transfer and storage device provided in the exemplary embodiment of the present disclosure;

[0034] Figure 2 is the overall structural schematic diagram of the bracket provided in the exemplary embodiment of the present disclosure;

[0035] Figure 3 is the structural schematic diagram of the first unmanned aerial vehicle and the second unmanned aerial vehicle stored in the bracket provided in the exemplary embodiment of the present disclosure;

[0036] Figure 4 is the structural schematic diagram of the first unmanned aerial vehicle stored in the bracket provided in the exemplary embodiment of the present disclosure;

[0037] Figure 5 is Figure 4 the enlarged schematic diagram of part A in

[0038] Figure 6It is a schematic diagram of the overall structure of the storage cabinet provided in the exemplary embodiment of the present disclosure;

[0039] Figure 7 It is a schematic diagram of the overall structure of the transfer cabinet provided in the exemplary embodiment of the present disclosure;

[0040] Figure 8 It is a schematic diagram of the overall structure of the vehicle body provided in the exemplary embodiment of the present disclosure;

[0041] Figure 9 is Figure 7 an enlarged schematic diagram of part C in;

[0042] Figure 10 is Figure 8 an enlarged schematic diagram of part D in;

[0043] Figure 11 A schematic diagram of the overall structure of the spare parts cabinet provided in the exemplary embodiment of the present disclosure.

[0044] Explanation of reference numerals

[0045] 1. Frame; 11. First unmanned aerial vehicle; 12. Second unmanned aerial vehicle; 13. First limiting part; 14. Second limiting part; 15. Column; 2. Support mechanism; 21. First support assembly; 211. First support part; 2111. First bearing groove; 212. Second support part; 213. Fifth support part; 2131. First opening groove; 214. First mating part; 22. Second support assembly; 221. Third support part; 2211. Second bearing groove; 222. Fourth support part; 223. Sixth support part; 224. Second mating part; 2231. Second opening groove; 3. Support beam; 4. Storage cabinet; 41. First cabinet body; 42. Storage rack; 43. Multi-stage slide rail; 5. Transfer cabinet; 51. Vehicle body; 52. Second cabinet body; 53. Transfer rack; 54. Guide part; 55. Sealing part; 56. Reinforcing part; 6. Spare parts cabinet; 61. Power supply; 62. Wireless communication module; 7. Wheels; 71. Floor feet. Detailed implementation manners

[0046] The following will describe the detailed implementation manners of the present disclosure in conjunction with the accompanying drawings. It should be understood that the detailed implementation manners described herein are only used to illustrate and explain the present disclosure, and are not used to limit the present disclosure.

[0047] In the present disclosure, for the sake of convenience in description, a first direction, a second direction, and a third direction are defined for the bracket. Among them, "X" represents the first direction, "Y" represents the second direction, and "Z" represents the third direction. Unless otherwise specified, "inside and outside" refer to the inside and outside of the contour of the corresponding component; "far and near" refer to the far and near in the spatial position of the corresponding component relative to another component. In addition, the terms "first", "second", etc. used in the present disclosure are used to distinguish one element from another element and do not have sequentiality and importance. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements.

[0048] The bracket and the drone hangar in the exemplary embodiments of the present disclosure will be described below with reference to the drawings.

[0049] According to a first aspect of the present disclosure, with reference to Figures 1 to 11 , the present disclosure provides a bracket for storing and / or transporting drones. The bracket includes a frame body 1 and a support mechanism 2. The frame body 1 has a first side and a second side opposite to each other in the first direction; the support mechanism 2 is connected to the frame body 1 and includes a first support assembly 21 and a second support assembly 22. The first support assembly 21 is used to support a first drone 11 that passes through the frame body 1 from the first side and extends to the second side, and the second support assembly 22 is used to support a second drone 12 that passes through the frame body 1 from the second side and extends to the first side. The first support assembly 21 and the second support assembly 22 arrange the first drone 11 and the second drone 12 in a staggered manner in the second direction, and the second direction is perpendicular to the first direction.

[0050] Through the above technical solutions, the transportation and / or storage of the unmanned aerial vehicle can be made more convenient. For example, the transportation efficiency is high, the storage space occupied is small, and the transportation and / or storage do not require repeated disassembly and assembly of the unmanned aerial vehicle. Specifically, by means of the bracket, at least the first unmanned aerial vehicle 11 and the second unmanned aerial vehicle 12 are stored, and the effect of saving space occupancy is particularly obvious. For example, the first unmanned aerial vehicle 11 and the second unmanned aerial vehicle 12 can be respectively placed on the bracket through the first support assembly 21 and the second support assembly 22. Among them, the first unmanned aerial vehicle 11 and the second unmanned aerial vehicle 12 partially penetrate the frame 1 in the first direction to realize storage extending from the first side to the second side or from the second side to the first side. Compared with being stored entirely on the first side or the second side, the occupied space in the first direction is reduced. At the same time, the first support assembly 21 and the second support assembly 22 enable the first unmanned aerial vehicle 11 and the second unmanned aerial vehicle 12 to be partially misaligned in the second direction. It can also be said that the projections of the first unmanned aerial vehicle 11 and the second unmanned aerial vehicle 12 in the first direction partially overlap. When storing, part of the structure of the first unmanned aerial vehicle 11 is located in the gap between different structures of the second unmanned aerial vehicle 12, and part of the structure of the second unmanned aerial vehicle 12 is located in the gap between different structures of the first unmanned aerial vehicle 11. Thus, the gap between different structures of the first unmanned aerial vehicle 11 and the second unmanned aerial vehicle 12 forms a storage space, enabling the first unmanned aerial vehicle 11 and the second unmanned aerial vehicle 12 to be partially misaligned in the second direction to reduce the occupied space in the second direction.

[0051] In an exemplary application scenario, for example, when using the bracket to store the unmanned aerial vehicle, a storage device can be set at the storage point / operation point. For example, the storage device can include a first cabinet 41 and a bracket. The bracket can be stored in the first cabinet 41 or at least partially taken out for the storage of the unmanned aerial vehicle. It is not necessary to repeatedly disassemble and assemble the unmanned aerial vehicle, and the space occupied by storing the unmanned aerial vehicle can be significantly reduced, and the storage cost is significantly reduced.

[0052] In another exemplary application scenario, for example, when using the bracket to transport the unmanned aerial vehicle, a transfer device can be set. For example, the transfer device can include a vehicle body 51, and the bracket is set on the vehicle body 51 to facilitate the transfer of the unmanned aerial vehicle. During the transfer process, it is not necessary to disassemble the unmanned aerial vehicle, and at least two unmanned aerial vehicles can be transferred simultaneously, significantly improving the transfer efficiency of the unmanned aerial vehicle.

[0053] In some embodiments, refer to Figures 2 to 5, the frame 1 may include at least two columns 15 arranged side by side and spaced apart in the second direction. Each column 15 is provided with a support mechanism 2. In the present disclosure, it is exemplarily described that the number of columns 15 is two. In this way, the first drone 11 is supported by two first support components 21, and the second drone 12 is supported by two second support components 22 to improve the stability of the bracket when supporting the first drone 11 and the second drone 12. In another embodiment, the number of columns 15 may also be four. For example, one group of the first drone 11 and the second drone 12 is placed on two of them, and another group of the first drone 11 and the second drone 12 is placed on the other two. The present disclosure is not limited to this.

[0054] The first support component 21 and the second support component 22 may be constructed in any suitable manner to be respectively used for supporting the first drone 11 and the second drone 12. For example, in some embodiments, referring to Figures 2 to 5 , the first support component 21 may include a first support portion 211 and a second support portion 212. The first support portion 211 is located on the first side and is used to support the arm or fuselage of the first drone 11. The second support portion 212 is located on the second side and is used to support the landing gear of the first drone 11. Similarly, the second support component 22 may include a third support portion 221 and a fourth support portion 222. The third support portion 221 is located on the second side and is used to support the arm or fuselage of the second drone 12. The fourth support portion 222 is located on the first side and is used to support the landing gear of the second drone 12. In this way, the first drone 11 and the second drone 12 are relatively stored on the bracket. In the first direction, the landing gear of the first drone 11 partially passes through the frame 1 from the first side, that is, between the two columns 15, or on one side of one column 15 away from the other column 15, and is supported by the second support portion 212 on the second side. The landing gear of the second drone 12 partially passes through the frame 1 from the second side, that is, between the two columns 15, or on one side of one column 15 away from the other column 15, and is supported by the fourth support portion 222 on the first side. Compared with the first drone 11 and the second drone 12 being respectively stored on the first side and the second side as a whole, the occupied space in the first direction is reduced; it can be understood that the landing gears are generally arranged in pairs. At least one landing gear of one of the first drone 11 and the second drone 12 is located in the gap between the two landing gears and the fuselage of the other. Thus, the first drone 11 and the second drone 12 can be arranged in a staggered manner in the second direction, and the projection parts of the first drone 11 and the second drone 12 in the first direction overlap partially, reducing the occupied space in the second direction.

[0055] In some embodiments, referring to Figure 2, the first support portion 211 and the third support portion 221 can be connected by a support beam 3 connected to the frame 1. It can be understood that, for example, the number of support beams 3 can be set to one, and the two free ends of the support beam 3 are respectively a first end located on the first side and a second end located on the second side. The first support portion 211 is connected to the first end of the support beam 3, and the second support portion 212 is connected to the second end of the support beam 3. In some other possible embodiments not shown in the drawings, the number of support beams 3 can be set to multiple and correspond one-to-one to the first support portion 211 and the third support portion 221. Thus, one end of the support beam 3 is connected to the frame 1, and the other end is for connecting the first support portion 211 or the third support portion 221. The present disclosure does not make specific limitations on this. It should be noted that one end of the support beam 3 close to the first support portion 211 can be partially bent to avoid the landing gear of the second unmanned aerial vehicle 12. Similarly, one end of the support beam 3 close to the third support portion 221 can be partially bent to avoid the landing gear of the first unmanned aerial vehicle 11. In addition, the support beam 3 can be detachably connected to the frame 1 in a way such as bolt connection, so as to be able to replace the first support portion 211 and the third support portion 221. At the same time, the position of the support beam 3 in the third direction is adjustable. For example, the frame 1 can be provided with a plurality of threaded holes at intervals in the third direction, and the support beam 3 is connected to different positions by bolts connecting different threaded holes, so as to be able to adaptively support unmanned aerial vehicles of different models. Among them, the third direction can be perpendicular to the first direction and the second direction. The present disclosure is not limited to this.

[0056] It can be understood that the first support portion 211 and the third support portion 221 can be constructed in any suitable manner to correspondingly support the arms or fuselages of the first unmanned aerial vehicle 11 and the second unmanned aerial vehicle 12. For example, the first support portion 211 can have a first bearing groove 2111 with an upward opening, and the first bearing groove 2111 is used to support the arm or fuselage of the first unmanned aerial vehicle 11; similarly, the third support portion 221 can have a second bearing groove 2211 with an upward opening, and the second bearing groove 2211 is used to support the arm or fuselage of the second unmanned aerial vehicle 12. Among them, Figures 3 to 5Exemplarily, an embodiment is shown in which the first receiving groove 2111 is used to support the arm of the first drone 11, and the second receiving groove 2211 is used to support the arm of the second drone 12. In other embodiments not shown, the first receiving groove 2111 and the second receiving groove 2211 may also be used to support the fuselage of the drone, and the present disclosure is not limited thereto. Alternatively, in some other possible embodiments not shown in the drawings, the first support portion 211 may include a first hook with an upward opening and a bent end portion, and the first hook may be used to hook the fuselage structure of the first drone 11, such as a bracket of a camera module, etc. The third support portion 221 may include a second hook with an upward opening and a bent end portion, and the second hook may be used to hook the fuselage mechanism of the second drone 12, such as a bracket of a camera module, etc. The present disclosure is not limited thereto.

[0057] Among them, the first receiving groove 2111 and the second receiving groove 2211 can be adaptively configured to fit the shape of the outer surfaces of the arms of the first drone 11 and the second drone 12. In this way, the first receiving groove 2111 can position and limit the first drone 11 in the first direction, and the second receiving groove 2211 can position and limit the second drone 12 in the first direction. In addition, in some other possible deformation manners not shown in the drawings, the groove walls forming the first receiving groove 2111 and the second receiving groove 2211 may be elastic. Taking the storage process of the first drone 11 as an example, during the process of placing the first drone 11 in the first receiving groove 2111, the two side groove walls of the first receiving groove 2111 in the first direction first move away from each other, and then move closer to each other until they fit and press against the first drone 11, so as to limit and fix the first drone 11 in the first direction. At the same time, the groove walls of the first receiving groove 2111 can extend in the third direction and can fit the outer surface of the upper half of the arm of the first drone 11 in the storage state, so as to be able to limit the first drone 11 in the third direction. The support and limiting effects of the second receiving groove 2211 on the second drone 12 are the same, and the present disclosure will not be elaborated herein.

[0058] In some embodiments, referring to Figure 2 , the second support portion 212 and the fourth support portion 222 can be connected to the frame 1 through a fixed substrate. The fixed substrate can be detachably connected to the frame 1 in forms such as bolt connection or bonding, etc., so as to be able to replace the second support portion 212 and the fourth support portion 222. At the same time, the position of the fixed substrate in the third direction is adjustable. For example, the frame 1 can be provided with a plurality of threaded holes at intervals in the third direction, and the fixed substrate is connected to different positions by bolts connecting different threaded holes, so as to be able to adaptively support drones of different models, where the third direction is perpendicular to the first direction and the second direction. The present disclosure is not limited thereto.

[0059] It can be understood that the second support part 212 and the fourth support part 222 can be constructed in any suitable manner for respectively supporting the landing gears of the first drone 11 and the second drone 12. For example, the second support part 212 can include a first rod connected to the frame 1 and extending along the first direction, and a second rod connected to the first rod and extending along the second direction, and the second rod is used to support the landing gear of the first drone 11. Similarly, the fourth support part 222 can include a third rod connected to the frame 1 and extending along the first direction, and a fourth rod connected to the third rod and extending along the second direction, and the fourth rod is used to support the landing gear of the second drone 12. Wherein, the second rod and the fourth rod can play a visual guiding role during the storage of the first drone 11 and the second drone 12 to assist in the preliminary positioning in the second direction, that is, when the first drone 11 is stored, the landing gear can be located at any position between the end of the second rod connected to the first rod and the free end, and when the second drone 12 is stored, the landing gear can be located at any position between the end of the fourth rod connected to the third rod and the free end. The present disclosure does not make specific limitations thereto.

[0060] In some embodiments, referring to Figures 2 to 5, the first support component 21 may further include a fifth support portion 213 located between the first support portion 211 and the second support portion 212 in the first direction. The fifth support portion 213 is used to fix the landing gear of the first drone 11; the second support component 22 may further include a sixth support portion 223 located between the third support portion 221 and the fourth support portion 222 in the first direction. The sixth support portion 223 is used to fix the landing gear of the second drone 12. In this way, the fifth support portion 213 cooperates with the second support portion 212 to support the landing gear of the first drone 11 and improve the stability during storage. The sixth support portion 223 cooperates with the fourth support portion 222 to support the landing gear of the second drone 12 and improve the stability during storage. Among them, the fifth support portion 213 is rotatably connected to the frame 1. The fifth support portion 213 has a first opening groove 2131. The first opening groove 2131 is used to sleeved or disengaged from the leg of the landing gear of the first drone 11 as the fifth support portion 213 rotates, so as to limit the first drone 11 in the third direction; similarly, the sixth support portion 223 is rotatably connected to the frame 1. The sixth support portion 223 has a second opening groove 2231. The second opening groove 2231 is used to sleeved or disengaged from the leg of the landing gear of the second drone 12 as the sixth support portion 223 rotates, so as to limit the second drone 12 in the third direction. It can be understood that the pivot axes of the fifth support portion 213 and the sixth support portion 223 during rotation may be parallel to the third direction. The third direction is perpendicular to the first direction and the second direction. The first opening groove 2131 and the second opening groove 2231 may extend perpendicular to the third direction. For example, when the first opening groove 2131 and the second opening groove 2231 are respectively sleeved on the legs of the landing gears of the first drone 11 and the second drone 12, the first opening groove 2131 and the second opening groove 2231 extend along the second direction.

[0061] It can be understood that when the first opening groove 2131 is sleeved on the leg of the landing gear of the first UAV 11, the lower side wall of the two side walls of the first opening groove 2131 along the third direction is used to abut and support the leg of the landing gear of the first UAV 11, and the upper side wall fits to stop the leg of the landing gear of the first UAV 11, so as to limit the first UAV 11 in the third direction; Similarly, when the second opening groove 2231 is sleeved on the leg of the landing gear of the second UAV 12, the lower side wall of the two side walls of the second opening groove 2231 along the third direction is used to abut and support the leg of the landing gear of the second UAV 12, and the upper side wall fits to stop the leg of the landing gear of the second UAV 12, so as to limit the second UAV 12 in the third direction. In addition, when the first opening groove 2131 and the second opening groove 2231 are respectively sleeved on the legs of the landing gears of the first UAV 11 and the second UAV 12, the bottom of the first opening groove 2131 can fit to stop the leg of the landing gear of the first UAV 11, and the bottom of the second opening groove 2231 can fit to stop the leg of the landing gear of the second UAV 12, so as to be able to position the first UAV 11 and the second UAV 12 in the second direction, and limit the first UAV 11 and the second UAV 12, so that there is a safety gap between the first UAV 11 and the second UAV 12, and the opening directions of the first opening groove 2131 and the second opening groove 2231 are opposite, so as to reduce the possibility that the first UAV 11 and the second UAV 12 move along the second direction during storage and collide with each other, resulting in structural damage.

[0062] In some other possible deformation modes not shown in the drawings, the pivot axis when the fifth support portion 213 and the sixth support portion 223 rotate can also deviate from the third direction. The first opening groove 2131 and the second opening groove 2231 can extend along a direction perpendicular to the pivot axis, and the openings of the first opening groove 2131 and the second opening groove 2231 face downward. Taking the first opening groove 2131 sleeved on the leg of the landing gear of the first UAV 11 as an example, the bottom of the first opening groove 2131 is located above the leg of the landing gear of the first UAV 11. In this way, the two side walls of the first opening groove 2131 parallel to the pivot axis and the bottom wall of the bottom part of the groove bottom can respectively limit the first UAV 11 in the second direction. At the same time, it can also at least partially fit the leg of the landing gear of the first UAV 11 in the third direction, so as to be able to support and limit the first UAV 11 in the third direction. The present disclosure does not make specific limitations on this.

[0063] In some embodiments, referring to Figures 2 to 5, the frame 1 may be provided with a first limiting portion 13 for limiting the rotation angle of the fifth supporting portion 213; similarly, the frame 1 may be provided with a second limiting portion 14 for limiting the rotation angle of the sixth supporting portion 223. It can be understood that the first limiting portion 13 and the second limiting portion 14 are respectively used to limit the rotation angles of the fifth supporting portion 213 and the sixth supporting portion 223, which means that the first limiting portion 13 and the second limiting portion 14 respectively limit the rotation of the fifth supporting portion 213 and the sixth supporting portion 223 after they are separated from the legs of the landing gears of the first UAV 11 and the second UAV 12, so as to prevent the fifth supporting portion 213 and the sixth supporting portion 223 from interfering with the access to the first UAV 11 and the second UAV 12. Among them, the first limiting portion 13 and the second limiting portion 14 can be adaptively configured according to the forms of the fifth supporting portion 213 and the sixth supporting portion 223. For example, the fifth supporting portion 213 and the sixth supporting portion 223 can be configured as clamping sleeves, and a first opening groove 2131 and a second opening groove 2231 are respectively formed on the two clamping sleeves. The first limiting portion 13 and the second limiting portion 14 can include baffles connected to the frame 1, and the baffles are arranged on the side of the fifth supporting portion 213 away from the first UAV 11 and on the side of the sixth supporting portion 223 away from the second UAV 12. In this way, the first limiting portion 13 can stop the fifth supporting portion 213 acting on the leg of the landing gear of the first UAV 11 separated therefrom, and the second limiting portion 14 can stop the sixth supporting portion 223 acting on the leg of the landing gear of the second UAV 12 separated therefrom. In addition, the first limiting portion 13 and the second limiting portion 14 can also respectively fix the fifth supporting portion 213 and the sixth supporting portion 223 to prevent the fifth supporting portion 213 and the sixth supporting portion 223 from separating. For example, taking the first limiting portion 13 and the fifth supporting portion 213 as an example, magnets can be respectively arranged on the first limiting portion 13 and the fifth supporting portion 213 to magnetically attract and fix the first limiting portion 13 and the fifth supporting portion 213, or a clamping block can be arranged on one of the first limiting portion 13 and the fifth supporting portion 213, and a clamping groove inserted and matched with the clamping block is formed on the other, so as to fix the first limiting portion 13 and the fifth supporting portion 213 by clamping and matching. The present disclosure is not limited thereto. Similarly, similar structures can be arranged on the second limiting portion 14 and the sixth supporting portion 223 to fix the second limiting portion 14 and the sixth supporting portion 223, and the present disclosure will not be described in detail herein.

[0064] According to a second aspect of the present disclosure, a storage device for storing drones is provided. The storage device includes a first cabinet 41 and the above-mentioned bracket. When storing drones, the storage device has all the beneficial effects of the above-mentioned bracket, and the present disclosure will not elaborate on this. In addition, the bracket is movably connected to the first cabinet 41 so as to be able to be pulled out from the first cabinet 41 or stored in the first cabinet 41. Among them, when the bracket is pulled out from the first cabinet 41, it is in the first position, and when the bracket is stored in the first cabinet 41, it is in the second position. In this way, in the first position, the bracket is located outside the first cabinet 41 to enable the access to and from the drones on the bracket, and in the second position, the bracket is located inside the first cabinet 41 to enable the sheltered storage of the drones. It can be understood that the bracket can be movably connected to the first cabinet 41 in any suitable manner. For example, the bracket can be connected to the first cabinet 41 through a multi-stage slide rail 43. An opening for the bracket to be pushed and pulled in and out is provided on the first cabinet 41, and a cabinet door that can shelter the opening is connected. Then the bracket can be connected to the cabinet door so that the bracket is in the first position for accessing and from the drones by pulling out the cabinet door, or the bracket is in the second position for storing the drones by pushing in the cabinet door. The present disclosure is not limited to this. In addition, the cabinet door can be lockingly attached to the first cabinet 41 through, for example, an electronic lock, and the present disclosure will not elaborate on this.

[0065] According to a third aspect of the present disclosure, a transfer device for transferring drones is provided. The transfer device includes a vehicle body 51 and the above-mentioned frame 1. When transferring drones, the transfer device has all the beneficial effects of the above-mentioned bracket, and the present disclosure will not elaborate on this. In addition, the frame 1 is provided on the vehicle body 51. In this way, at least one drone can be stored on the bracket and placed on the vehicle body 51, and then the damaged drones can be transported by the vehicle body 51 for repair, or the drones can be transported to change the usage location. In addition, the transfer device further includes a second cabinet 52. The second cabinet 52 has an accommodation space for accommodating the vehicle body 51 and the bracket and a closable opening for the vehicle body 51 and the bracket to enter and exit the accommodation space. In this way, the vehicle body 51 can enter and be temporarily stored in the accommodation space in the second cabinet 52 through the opening, and then the second cabinet 52 can shelter the vehicle body 51, the bracket, and the drones stored on the bracket to reduce the influence of the external environment on the drones, such as the possibility of being soaked by rain and eroded by impurity particles resulting in damage.

[0066] In some embodiments, referring to Figure 2, the first support part 211 of the first support assembly 21 for supporting the arm of the first drone 11 can be detachably connected with a first mating part 214, and the first mating part 214 cooperates with the first support part 211 to clamp the arm; similarly, the third support part 221 of the second support assembly 22 for supporting the arm of the second drone 12 can be detachably connected with a second mating part 224, and the second mating part 224 cooperates with the third support part 221 to clamp the arm. In this way, when storing the first drone 11 on the bracket, the first drone 11 can be supported by the first support part 211, and at the same time, the first mating part 214 cooperates with the first support part 211 to limit and fix the arm of the first drone 11 in the third direction, so as to improve the stability of the vehicle body 51 when transporting the first drone 11 and storing it on the bracket. Similarly, when storing the second drone 12 on the bracket, the second drone 12 can be supported by the third support part 221, and at the same time, the second mating part 224 cooperates with the third support part 221 to limit and fix the arm of the second drone 12 in the third direction, so as to improve the stability of the vehicle body 51 when transporting the second drone 12 and storing it on the bracket. It can be understood that the first mating part 214 can also be detachably connected to the second support part 212, so as to cooperate with the second support part 212 to limit and fix the landing gear of the first drone 11 in the third direction, so as to improve the stability of the vehicle body 51 when transporting the first drone 11 and storing it on the bracket. The second mating part 224 can also be detachably connected to the fourth support part 222, so as to cooperate with the fourth support part 222 to limit and fix the landing gear of the second drone 12 in the third direction, so as to improve the stability of the vehicle body 51 when transporting the second drone 12 and storing it on the bracket. The present disclosure is not limited thereto. Among them, the first mating part 214 and the first support part 211, as well as the second mating part 224 and the third support part 221, can be detachably connected by means such as bolt connection or snap connection, and the present disclosure does not make specific limitations on this. In addition, when the bracket is applied to the storage device, the first mating part 214 and the second mating part 224 can also be provided to be used for stabilizing the storage of the first drone 11 and the second drone 12, and the present disclosure is not limited thereto.

[0067] According to a fourth aspect of the present disclosure, there is provided a drone hangar, including a storage cabinet 4, a transfer cabinet 5 and a spare parts cabinet 6.

[0068] Among them, the storage cabinet 4 may include a first cabinet body 41 and a storage rack 42. The storage rack 42 may be configured as or include the bracket provided in the above first aspect. The bracket is movably connected to the first cabinet body 41 so as to be able to be pulled out from or received into the first cabinet body 41. Among them, the bracket may be movably connected to the first cabinet body 41 through, for example, a multi-stage slide rail 43. The first cabinet body 41 may also be movable. For example, walking wheels are provided on the first cabinet body 41 so that the storage cabinet 4 can also be moved integrally to transport the drone. In addition, the storage cabinet 4 may be the storage device provided in the above second aspect.

[0069] The transfer cabinet 5 may include a second cabinet body 52, a vehicle body 51, and a transfer rack 53 provided on the vehicle body 51. The transfer rack 53 may be configured as or include the bracket provided in the above first aspect. For example, the transfer rack 53 may include a bracket and a frame for strengthening the connection between the bracket and the vehicle body 51, and the present disclosure does not make specific limitations thereto. The second cabinet body 52 has an accommodation space for accommodating the vehicle body 51 and the bracket and a closable opening for the vehicle body 51 and the bracket to enter and exit the accommodation space. Among them, the opening may be opened and closed through, for example, a cabinet door. In addition, the transfer cabinet 5 may be the transfer device provided in the above third aspect.

[0070] In some embodiments, referring to Figures 7 to 10 , a guiding member 54 capable of acting on the frame to guide the vehicle body 51 through the opening is provided at the closable opening of the second cabinet body 52. The guiding member 54 may be a roller connected to the second cabinet body 52. In this way, for example, when the vehicle body 51 storing a drone needs to pass through the opening to enter the second cabinet body 52 for temporary storage, the frame of the vehicle body 51 contacts the roller, and during the process of the vehicle body 51 moving towards the inside of the second cabinet body 52, the roller rolls to guide the vehicle body 51 to move through the frame. In addition, a sealing member 55 is connected to the bottom of the second cabinet body 52. The sealing member 55 is used for contacting and cooperating with the frame so that when the vehicle body 51 is temporarily stored inside the transfer cabinet 5, the bracket is isolated from the outside under the action of the vehicle body 51, the sealing member 55, and the cabinet wall of the transfer cabinet 5, so as to reduce the influence of the external environment on the drone, such as the possibility of being soaked by rain and eroded by impurity particles resulting in damage. It can be understood that in order to facilitate the entry and exit of the vehicle body 51, the second cabinet body 52 has no bottom wall. Therefore, a reinforcing member 56 may be connected between the two side cabinet walls in the horizontal direction forming the opening to improve the overall structural strength of the transfer cabinet 5. At the same time, the height of the reinforcing member 56 is adjustably connected to the second cabinet body 52 to cooperate with the floor feet 71 (described in detail below) to adjust the height of the transfer cabinet 5.

[0071] In some embodiments, referring to Figure 1, the storage cabinet 4, the transfer cabinet 5 and the spare parts cabinet 6 are arranged side by side and detachably connected. For example, they can be detachably connected by means of a connecting plate and bolt fastening. One of the adjacent storage cabinet 4, transfer cabinet 5 and spare parts cabinet 6 is connected with a connecting plate, and the connecting plate is threadedly connected with the other by bolts to fix the two. It can be understood that the exit of the first cabinet body 41 for the storage rack 42 to move in and out (the above-mentioned opening for the bracket to be pushed and pulled in and out) and the exit of the second cabinet body 52 for the vehicle body 51 and the transfer rack 53 to move in and out (the above-mentioned closable opening) are located on the same side of the UAV hangar. In this way, since a space for pushing and pulling the bracket needs to be reserved outside the first cabinet body 41 and a space for the vehicle body 51 to enter and exit needs to be reserved outside the second cabinet body 52, thus, setting the exits of the storage cabinet 4 and the transfer cabinet 5 on the same side can reduce the occupied space of the UAV hangar, and at the same time, it is also convenient for the storage and retrieval of UAVs and the maintenance of the storage cabinet 4 and the transfer cabinet 5. In addition, referring to Figure 1 , Figure 6 , Figure 7 and Figure 11 , wheels 7 and floor feet 71 can be integrally installed at the bottoms of the storage cabinet 4, the transfer cabinet 5 and the spare parts cabinet 6 for the movement and fixation of the storage cabinet 4, the transfer cabinet 5 and the spare parts cabinet 6. At the same time, the floor feet 71 can also adjust the height of the storage cabinet 4, the transfer cabinet 5 and the spare parts cabinet 6.

[0072] In some embodiments, referring to Figure 1 , for the convenience of the use and maintenance of the storage cabinet 4, the transfer cabinet 5 and the spare parts cabinet 6, the storage cabinet 4 can be arranged between the transfer cabinet 5 and the spare parts cabinet 6 and the number of the storage cabinets 4 can be set to be multiple. Among them, the spare parts cabinet 6 is used for storing and retrieving the spare parts of the UAV, and its opening faces away from the storage cabinet 4 and the transfer cabinet 5, and the size of the opening for storing and retrieving the spare parts can be enlarged to facilitate the storage and retrieval of the spare parts of the UAV. In addition, referring to Figure 11, a spare parts cabinet 6 is also provided with a power supply 61, a wireless communication module 62 and a data uploading system. Power supply interfaces connected to the power supply 61 are provided in the storage cabinet 4 and the transfer cabinet 5, and the power supply interfaces are used for power supply and / or signal transmission of the unmanned aerial vehicle. In addition, a wireless network is established through the power supply 61, the wireless communication module 62 and the data uploading system. The data uploading system may include a computer, such as a computer, and the computer has data uploading software, such as software for automatically recording work logs. After entering, the ID of the unmanned aerial vehicle that has connected to the wireless network can be seen, and then data, such as the unmanned aerial vehicle log, can be downloaded. Among them, the computer can be signal-connected to the unmanned aerial vehicle through the wireless communication module 62 (i.e., the wireless network) to download data, or can also achieve wired signal transmission through the power supply interface to download data. Alternatively, it is also possible that the computer can be connected to the cloud through the wireless communication module 62 to transmit data to the cloud. It can be understood that, for the convenience of wiring of electrical connections, the power lines between the spare parts cabinet 6 and the storage cabinet 4, the power lines between two adjacent storage cabinets 4, and the power lines between the storage cabinet 4 and the transfer cabinet 5 can all be arranged outside the cabinet, and power supply interfaces are reserved for the power lines inside the cabinet. The present disclosure does not make specific limitations on this.

[0073] The present disclosure exemplarily describes the use process of the unmanned aerial vehicle stored on the bracket.

[0074] Thread the first unmanned aerial vehicle 11 through the bracket from the first side to the second side along the first direction, wherein one landing gear is threaded between the two columns 15. The first bearing groove 2111 is used to support the arm of the first unmanned aerial vehicle 11, and the second rod is used to support the landing gear of the first unmanned aerial vehicle 11. Rotate the fifth support part 213 so that the first opening groove 2131 is sleeved on the leg of the landing gear of the first unmanned aerial vehicle 11.

[0075] Thread the second unmanned aerial vehicle 12 through the bracket from the second side to the first side along the first direction, wherein one landing gear is threaded between the two columns 15. The second bearing groove 2211 is used to support the arm of the second unmanned aerial vehicle 12, and the fourth rod is used to support the landing gear of the second unmanned aerial vehicle 12. Rotate the sixth support part 223 so that the second opening groove 2231 is sleeved on the leg of the landing gear of the second unmanned aerial vehicle 12.

[0076] The preferred embodiments of the present disclosure have been described in detail above with reference to the accompanying drawings. However, the present disclosure is not limited to the specific details in the above embodiments. Within the scope of the technical concept of the present disclosure, various simple modifications can be made to the technical solutions of the present disclosure, and these simple modifications all belong to the protection scope of the present disclosure.

[0077] In addition, it should be noted that, among the various specific technical features described in the above specific embodiments, they can be combined in any suitable manner without conflict. To avoid unnecessary repetition, the present disclosure will not separately describe various possible combination methods.

[0078] In addition, any combination can be made among various different embodiments of the present disclosure, as long as it does not violate the idea of the present disclosure, and it should equally be regarded as the content disclosed by the present disclosure.

Claims

1. A bracket, characterized in that, For storing and / or transporting drones, the bracket includes: A frame body having a first side and a second side opposite to each other in a first direction; and A support mechanism connected to the frame body and including a first support component and a second support component. The first support component is used to support a first drone that partially passes through the frame body from the first side and extends to the second side, and the second support component is used to support a second drone that partially passes through the frame body from the second side and extends to the first side. The first support component and the second support component arrange the first drone and the second drone in a partially misaligned manner in a second direction perpendicular to the first direction.

2. The bracket according to claim 1, characterized in that, The first support component includes a first support portion and a second support portion. The first support portion is located on the first side and is used to support the arm or fuselage of the first drone, and the second support portion is located on the second side and is used to support the landing gear of the first drone; And / or The second support component includes a third support portion and a fourth support portion. The third support portion is located on the second side and is used to support the arm or fuselage of the second drone, and the fourth support portion is located on the first side and is used to support the landing gear of the second drone.

3. The bracket according to claim 2, characterized in that, The first support portion and the third support portion are connected by a support beam connected to the frame body; and / or The first support portion has a first bearing groove with an upward opening, and the first bearing groove is used to support the arm or fuselage of the first drone; And / or The third support portion has a second bearing groove with an upward opening, and the second bearing groove is used to support the arm or fuselage of the second drone.

4. The bracket according to claim 2, characterized in that, The first support component further includes a fifth support portion located between the first support portion and the second support portion in the first direction, and the fifth support portion is used to fix the landing gear of the first drone; and / or The second support component further includes a sixth support portion located between the third support portion and the fourth support portion in the first direction, and the sixth support portion is used to fix the landing gear of the second drone.

5. The bracket according to claim 4, wherein The fifth support portion is rotatably connected to the frame body, and the fifth support portion has a first opening groove, and the first opening groove is used to sleeved or disengaged from the leg of the landing gear of the first drone as the fifth support portion rotates, so as to limit the first drone in a third direction; And / or The sixth support portion is rotatably connected to the frame body, and the sixth support portion has a second opening groove, and the second opening groove is used to sleeved or disengaged from the leg of the landing gear of the second drone as the sixth support portion rotates, so as to limit the second drone in a third direction.

6. The bracket according to claim 5, characterized in that The frame body has a first limiting portion for limiting the rotation angle of the fifth support portion; and / or The frame body has a second limiting portion for limiting the rotation angle of the sixth support portion.

7. The bracket according to claim 2, wherein The first support portion is detachably connected with a first fitting portion, and the first fitting portion cooperates with the first support portion to clamp the arm; and / or The third support part is detachably connected with a second mating part, and the second mating part cooperates with the third support part to clamp the machine arm.

8. The stent according to any one of claims 1-7, characterized in that, The frame body includes at least two upright columns arranged side by side and spaced apart along the second direction, and each of the upright columns is provided with the support mechanism.

9. An unmanned aerial vehicle hangar, characterized in that, Comprising: A storage cabinet, which includes a first cabinet body and the bracket according to any one of claims 1-8, and the bracket is movably connected to the first cabinet body so as to be able to be pulled out from or received into the first cabinet body; A transfer cabinet, which includes a second cabinet body, a vehicle body and the bracket according to any one of claims 1-8 provided on the vehicle body; the second cabinet body has an accommodation space for accommodating the vehicle body and the bracket and a closable opening for the vehicle body and the bracket to enter and exit the accommodation space; And A spare parts cabinet for placing spare parts of the drone; Wherein, the storage cabinet, the transfer cabinet and the spare parts cabinet are arranged side by side and detachably connected.

10. The drone hangar according to claim 9, wherein, A power supply is arranged in the spare parts cabinet, and a power supply interface connected to the power supply is arranged in the storage cabinet and the transfer cabinet; and / or, A wireless communication module is arranged in the spare parts cabinet; and / or, A data uploading system is arranged in the spare parts cabinet.

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