Drones

Abstract

The present invention discloses an unmanned aerial vehicle, which comprises: a fuselage module, comprising a first panel and a load hanging part arranged on the inner side of the first panel, the load hanging part is provided with a limit card hole, the limit card hole comprises a free section and a locking section connected to each other, the aperture of the limit card hole at the free section is larger than the aperture at the locking section; a load module, comprising a second panel and a load mounting part arranged on the inner side of the second panel, the load mounting part is used to install the load, the load mounting part is provided with a limit pin, the limit pin can pass through the free section and be stuck in the locking section; and a locking module, comprising a first locking part and a second locking part that are detachably connected, the first locking part is connected to the first panel, and the second locking part is connected to the second panel. The technical solution of the present invention aims to realize a detachable connection between the fuselage module and the load module, so that a drone can replace different loads and perform different tasks, thereby expanding the application range of a single drone.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicles (UAVs), and in particular to a UAV. Background Art

[0002] With the development of drone technology, drones are increasingly used in mapping, geological surveys, disaster monitoring, meteorological detection, air traffic control, border patrol monitoring, emergency rescue, logistics, and military applications. The role of payloads in drones is crucial. When drones perform different tasks, they need to be equipped with different payloads to meet the functional requirements of drones. Existing drones generally include a fuselage module and a payload module. After the payload is installed in the payload module, it is hoisted on the fuselage module together. However, in the prior art, the fuselage module and the payload module are non-detachably connected, and the payload that can be carried on a drone is limited, resulting in a single application range for a single drone. Summary of the invention

[0003] The main purpose of the present invention is to provide a UAV, aiming to achieve a detachable connection between a fuselage module and a payload module, so that a UAV can replace different payloads and perform different tasks, thereby expanding the application range of a single UAV.

[0004] To achieve the above-mentioned purpose, the drone proposed by the present invention comprises:

[0005] The fuselage module comprises a first panel and a load hanging member arranged inside the first panel, the load hanging member is provided with a limit clamping hole, the limit clamping hole comprises a free section and a locking section connected to each other, and the aperture of the limit clamping hole at the free section is larger than the aperture of the locking section;

[0006] A load module, comprising a second panel and a load mounting member disposed inside the second panel, the load mounting member being used to mount a load, the load mounting member being provided with a limit pin, the limit pin being able to pass through the free section and be clamped into the locking section; and

[0007] The locking module includes a first locking member and a second locking member that are detachably connected; the first locking member is connected to the first panel, the second locking member is connected to the second panel, and when the first locking member is connected to the second locking member, the limit pin is limited to the locking section to lock the load module with the fuselage module.

[0008] Optionally, the first locking member is a locking screw, and the second locking member is a locking nut. The locking screw is arranged on the first panel, and the second panel is provided with a screw hole for the locking screw to pass through. The locking nut is connected to the side of the second panel facing away from the first panel and is locked to the locking screw.

[0009] Optionally, the locking nut is a hand-tightened nut.

[0010] Optionally, a mounting angle code is provided on a side of the first panel, and the locking screw is installed on the mounting angle code.

[0011] Optionally, a limiting ring groove is provided on the limiting pin, and the hole wall of the locking section is clamped in the limiting ring groove.

[0012] Optionally, the load hanging component is provided with a retaining rib extending along the periphery of the free section to limit the hole wall of the free section from being stuck in the limiting ring groove.

[0013] Optionally, the limiting pin comprises a head and a pin body connected to each other, and an end of the pin body close to the head is provided with a first convex ring protruding outwardly, and the limiting ring groove is limited between the first convex ring and the head.

[0014] Optionally, the load module further comprises a mounting nut, and the limiting pin is threadedly connected to the mounting nut to be locked and connected to the load mounting member.

[0015] Optionally, the mounting nut is pre-embedded in the load mounting member.

[0016] Optionally, a second convex ring is protruding outwardly from one end of the pin body away from the head, and the second convex ring and the mounting nut are arranged on opposite sides of the load mounting member.

[0017] Optionally, the first panel limits a mounting groove, and the second panel is adapted to cover a notch of the mounting groove to limit a receiving cavity between the first panel and the second panel, and the receiving cavity is used to accommodate the load hanging component, the load mounting component and the load.

[0018] Optionally, the first panel further includes a reinforcing flange extending along a notch of the mounting slot, and the reinforcing flange protrudes toward the inside of the mounting slot.

[0019] Optionally, the reinforcing flange includes two first flanges that are relatively protruding, and opposite sides of the load hanging component are bonded to the two first flanges.

[0020] Optionally, a reinforcement plate is further provided on the load hanging component, and the reinforcement plate is arranged close to the limit clamping hole and extends in a direction away from the load module.

[0021] Optionally, the load hanging member is further provided with a connection hole arranged close to the limit clamping hole, and the reinforcing plate is provided with a connection groove;

[0022] The reinforcing plate is inserted from the connecting hole, and the hole wall of the connecting hole is stuck in the connecting groove to be mortise-joined with the load hanging component.

[0023] Optionally, the fuselage module also includes a first connector arranged on the load hanging component, and the load module also includes a second connector arranged on the load mounting component, and the second connector is used to be electrically connected to the load; when the limit pin is stuck in the locking section, the first connector contacts and is connected to the second connector; when the limit pin is located in the free section, the second connector is separated from the first connector.

[0024] Optionally, the load hanging component is provided with a first mounting seat, the first connector is mounted on the first mounting seat, and the first mounting seat is detachably connected to the load hanging component.

[0025] Optionally, the first connector can be detachably mounted on the first mounting seat.

[0026] Optionally, the load mounting member is provided with a second mounting seat, the second connector is mounted on the second mounting seat, and the second mounting seat is detachably connected to the load mounting member.

[0027] Optionally, the second connector can be detachably mounted on the second mounting seat.

[0028] In the technical solution of the present invention, the payload module is detachably connected to the fuselage module, and the payload module can be removed separately to facilitate the replacement of the payload installed on the payload mounting member. In this way, a single unmanned aerial vehicle can carry different payloads to perform different tasks, thereby expanding the application scope of a single unmanned aerial vehicle. Specifically, the payload mounting member of the payload module and the payload hanging member of the fuselage module are detachably connected through the cooperation of the limit pin and the limit card hole, and the second panel of the payload module is detachably connected to the first panel of the fuselage module through the locking module, thereby realizing the detachable connection between the fuselage module and the payload module. In addition, the first panel of the fuselage module and the load hanging member are respectively connected to the second panel and the payload mounting member of the payload module, that is, the fuselage module and the payload module are connected through at least two structures, which is conducive to ensuring the connection stability between the fuselage module and the payload module. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0030] Figure 1 This is an overall assembly diagram of an embodiment of a drone of the present invention;

[0031] Figure 2 It is an overall assembly diagram of an embodiment of a fuselage module of a drone of the present invention;

[0032] Figure 3 The overall assembly diagram of the payload module of the UAV of the present invention is

[0033] Figure 4 It is a partial structural exploded view of an embodiment of a fuselage module of a drone of the present invention;

[0034] Figure 5 It is a structural exploded view of an embodiment of a payload module of a UAV of the present invention;

[0035] Figure 6 It is a schematic structural diagram of the limit pin of the UAV of the present invention;

[0036] Figure 7 This is a schematic diagram of the internal structure of the drone of the present invention when it is disassembled;

[0037] Figure 8 This is a schematic diagram of the internal structure of the drone of the present invention when it is installed.

[0038] Description of Figure Numbers:

[0039] Label name Label name 100 Body module 200 Load Module 110 First Panel 210 Second Panel 111 Mounting slot 220 Load mounting parts 112 Strengthen the flange 230 Limit pin 1121 First Flanging 231 Limiting ring groove 120 Load lifting parts 232 head 121 Limiting card hole 233 Pin 1211 Free segment 234 First convex ring 1212 Locking section 235 Second raised ring 122 Rebar 240 Mounting Nut 123 Connection hole 250 Second connector 130 Reinforcement plate 251 Second Mount 131 Connection slot 300 Locking module 150 First Connector 311 Locking screw 151 First Mount 321 Lock nut 322 Locking washers 323 Install the corner bracket

[0040] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0041] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0042] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, back, etc.), the directional indications are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0043] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present invention, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, if the meaning of "and / or" appearing in the full text is to include three parallel schemes, taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme that satisfies both A and B. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0044] The invention provides a drone.

[0045] In one embodiment of the present invention, Figures 1 to 3 As shown, the drone includes:

[0046] The fuselage module 100 includes a first panel 110 and a load hanging member 120 disposed inside the first panel 110, wherein the load hanging member 120 is provided with a limit hole 121, wherein the limit hole 121 includes a free section 1211 and a locking section 1212 connected to each other, and wherein the aperture of the limit hole 121 at the free section 1211 is larger than the aperture of the locking section 1212;

[0047] The load module 200 includes a second panel 210 and a load mounting member 220 disposed inside the second panel 210, wherein the load mounting member 220 is used to mount a load, and the load mounting member 220 is provided with a limit pin 230, wherein the limit pin 230 can pass through the free section 1211 and be inserted into the locking section 1212; and

[0048] The locking module 300 includes a first locking member and a second locking member that are detachably connected; the first locking member is connected to the first panel 110, the second locking member is connected to the second panel 210, and the first locking member is connected to the second locking member, so that the limit pin 230 can be limited to the locking section 1212 to lock the load module 200 and the fuselage module 100.

[0049] In the present invention, if Figure 7 As shown, when replacing the load, the first locking member and the second locking member can be disassembled first, and then the limit pin 230 can be withdrawn from the locking section 1212 to the free section 1211, and the limit pin 230 can be passed through the free section 1211, thereby completing the disassembly of the fuselage module 100 and the load module 200. At this time, the load on the load mounting member 220 can be replaced.

[0050] After the load installation is completed, first install the load installation member 220 on the load hanging member 120. Specifically, make the limit pin 230 pass through the limit clamp hole 121 from the free section 1211, and then lock it into the locking section 1212. After that, connect the first locking member with the second locking member to fix the first panel 110 and the second panel 210. In this way, the limit pin 230 will also be limited in the locking section 1212 to ensure the stable connection between the load installation member 220 and the load hanging member 120. In this way, the stable connection between the load module 200 and the fuselage module 100 is completed. The matching relationship between the various structures is as follows: Figure 8 shown.

[0051] In the present invention, the payload module 200 is detachably connected to the fuselage module 100, and the payload module 200 can be removed separately to facilitate replacement of the payload installed on the payload mounting member 220. In this way, a single drone can carry different payloads to perform different tasks, thereby expanding the application range of a single drone. Specifically, the payload mounting member 220 of the payload module 200 and the payload hanging member 120 of the fuselage module 100 are detachably connected through the cooperation of the limit pin 230 and the limit clamping hole 121, and the second panel 210 of the payload module 200 and the first panel 110 of the fuselage module 100 are detachably connected through the locking module 300, thereby realizing the detachable connection between the fuselage module 100 and the payload module 200. In addition, the first panel 110 and the load hanging component 120 of the fuselage module 100 are respectively connected to the second panel 210 and the load mounting component 220 of the load module 200, that is, the fuselage module 100 and the load module 200 are connected through at least two structures, which is conducive to ensuring the connection stability between the fuselage module 100 and the load module 200.

[0052] Furthermore, in this embodiment, if Figure 2 and Figure 3As shown, the first locking member is a locking screw 311, and the second locking member is a locking nut 321. The locking screw 311 is arranged on the first panel 110, and the second panel 210 is provided with a screw hole for the locking screw 311 to pass through. The locking nut 321 is connected to the side of the second panel 210 away from the first panel 110 and is locked to the locking screw 311. It can be understood that the locking screw 311 and the locking nut 321 should be arranged on the same side. When the limit pin 230 passes through the limit card hole 121 from the free section 1211, the locking screw 311 will also be aligned with the screw hole; when the limit pin 230 is inserted into the locking section 1212 from the free section 1211, the locking screw 311 will also pass through the screw hole; when the limit pin 230 is stuck in the locking section 1212, at this time, the locking nut 321 is connected to the locking screw 311, and the locking nut 321 is made to abut against the outer side of the second panel 210, so that the limit pin 230 can be limited to the locking section 1212, so that the load module 200 and the fuselage module 100 can be stably connected. Of course, in other embodiments, the first locking member may be a locking buckle provided on the first panel, and the second locking member may be a locking socket provided on the second panel. When the limit pin is inserted into the locking section from the free section 1211, the locking buckle is also correspondingly inserted into the locking socket.

[0053] Furthermore, in this embodiment, if Figure 2 As shown, the first panel 110 limits the installation groove 111, and the second panel 210 is adapted to cover the notch of the installation groove 111 to limit the accommodation cavity between the first panel 110 and the second panel 210, and the accommodation cavity is used to accommodate the load hanging member 120, the load mounting member 220 and the load. In this way, the main components of the drone are all inside the body, reducing the protrusions outside the first panel 110 and the second panel 210 to avoid adding aerodynamic resistance to the flight of the drone, which plays a role in increasing the flight time, and the appearance of the drone arranged in this way can also be improved. Furthermore, the external structure of the body formed by the combination of the first panel 110 and the second panel 210 is streamlined to further reduce the aerodynamic resistance of the drone during flight.

[0054] Furthermore, in this embodiment, if Figure 2 As shown, the first panel 110 further includes a reinforcing flange 112 extending along the notch of the mounting groove 111, and the reinforcing flange 112 is convexly arranged toward the mounting groove 111. It can be understood that after the load module 200 is installed in the fuselage module 100, the second panel 210 will be matched with the reinforcing flange 112 of the first panel 110, thereby, the arrangement of the reinforcing flange 112 is conducive to increasing the structural stability of the first panel 110 and the connection stability between the first panel 110 and the second panel 210.

[0055] Furthermore, in this embodiment, if Figure 2 and Figure 7 As shown, the reinforcing flange 112 includes two first flanges 1121 that are relatively protruding, and the opposite sides of the load hanging member 120 are bonded to the two first flanges 1121. Without loss of generality, in this embodiment, the load hanging member 120 is set as a square frame-shaped plate-like structure, and one of the frame bars also has an opening, and the two frame bars adjacent to the opening are bonded to the two first flanges 1121 by bonding to achieve a fixed connection between the load hanging member 120 and the first panel 110. Of course, in other embodiments, the two frame bars of the load hanging member can also be connected to the two first flanges by screw locking.

[0056] Furthermore, in this embodiment, if Figure 4 As shown, a reinforcing plate 130 is further provided on the load hanging part 120. The reinforcing plate 130 is arranged close to the limiting card hole 121 and extends in the direction away from the load module 200 to enhance the structural stability of the hole wall of the limiting card hole 121. In particular, the reinforcing plate 130 needs to be arranged close to the locking section 1212. It can be understood that the groove wall of the locking section 1212 needs to cooperate with the limiting ring groove 231, which is the main force-bearing part of the limiting card hole 121. The reinforcing plate 130 arranged close to the locking section 1212 can effectively increase the structural strength of the location to avoid the hole wall of the locking section 1212 from breaking, which affects the cooperation between the limiting pin 230 and the locking section 1212. Without loss of generality, in this embodiment, in order to improve the connection stability between the load hanging part 120 and the load mounting part 220, four limit pins 230 and limit holes 121 are correspondingly provided, and a limit hole 121 is provided at each of the four corners of the load hanging part 120, wherein two limit holes 121 are arranged close to the opening, and correspondingly, two reinforcing plates 130 are respectively arranged near the locking sections 1212 of the two limit holes 121, and the other two limit holes 121 are arranged on the same frame bar opposite to the opening, and correspondingly, a reinforcing plate 130 arranged on the frame bar will be arranged close to the locking sections 1212 of the two limit holes 121 at the same time. Furthermore, the plate body of the reinforcing plate 130 is a porous structure to reduce the weight of the reinforcing plate 130 itself, thereby preventing the reinforcing plate 130 from bringing excessive load to the load hanging part 120.

[0057] Furthermore, in this embodiment, if Figure 4As shown, the load hanging member 120 is also provided with a connection hole 123 arranged near the limit clamping hole 121, and the reinforcing plate 130 is provided with a connection groove 131; the reinforcing plate 130 is inserted from the connection hole 123, and the hole wall of the connection hole 123 is clamped in the connection groove 131, so as to be mortised to the load hanging member 120. Such a configuration can facilitate the installation of the reinforcing plate 130, and is conducive to the stable connection between the reinforcing plate 130 and the load hanging member 120. Of course, in other embodiments, the reinforcing plate can also be connected to the load hanging member by means of screw locking or snap connection.

[0058] Furthermore, in this embodiment, the locking nut 321 is a hand-tightening nut. In this way, the locking nut 321 and the locking screw 311 can be disassembled and assembled by hand-tightening without the need for other tools, thereby improving the convenience of disassembly and assembly of the fuselage module 100 and the load module 200. Furthermore, in order to improve the connection stability between the hand-tightening nut and the locking screw 311, an anti-loosening washer 322 can also be provided between the hand-tightening nut and the second panel 210. Preferably, the anti-loosening washer 322 is made of rubber material to prevent the hand-tightening nut from scratching the second panel 210.

[0059] Furthermore, in this embodiment, if Figure 2 As shown, the side of the first panel 110 is provided with a mounting angle code 323, and the locking screw 311 is installed on the mounting angle code 323 to achieve the connection between the locking screw 311 and the first panel 110. In this way, the installation of the locking screw 311 does not need to be limited by the structure of the first panel 110, and the protruding part of the mounting angle code 323 is small, and it will hardly cause interference in the installation and removal of the load module 200 and the fuselage module 100. Without loss of generality, in this embodiment, the mounting angle code 323 is installed on the side of the first flange 1121 away from the load hanging part 120, and there is a distance between the mounting angle code 323 and the outer edge of the first flange 1121. When the distance is approximately equal to the wall thickness of the second panel 210, after the locking screw 311 is locked with the hand nut, there will be almost no gap at the matching position of the first panel 110 and the second panel 210, so that the first panel 110 and the second panel 210 are integrated, thereby further improving the appearance of the drone.

[0060] Furthermore, in this embodiment, if Figure 6As shown, the limiting pin 230 is provided with a limiting annular groove 231, and the hole wall of the locking section 1212 is stuck in the limiting annular groove 231. Without loss of generality, in this embodiment, the limiting pin 230 includes a head 232 and a pin body 233 connected to each other, and the end of the pin body 233 close to the head 232 is protruding outward with a first convex ring 234, and the limiting annular groove 231 is limited between the first convex ring 234 and the head 232. In this way, by making the hole wall of the locking section 1212 stuck in the limiting annular groove 231, the relative displacement of the load hanging component 120 and the load mounting component 220 in the axial direction of the limiting pin 230 can be avoided, so that the limiting pin 230 can be reliably stuck in the locking section 1212, thereby improving the connection stability between the load hanging component 120 and the load mounting component 220. Without loss of generality, in this embodiment, the limiting pin 230 includes a head 232 and a pin body 233 connected to each other, and the end of the pin body 233 close to the head 232 is provided with a first protruding ring 234 protruding outwardly, and the limiting ring groove 231 is limited between the first protruding ring 234 and the head 232.

[0061] Furthermore, in this embodiment, if Figure 4 , Figure 7 and Figure 8 As shown, the load hanging part 120 is provided with a retaining rib 122 extending along the periphery of the free section 1211 to limit the hole wall of the free section 1211 from being stuck in the limiting ring groove 231, thereby avoiding the hole wall of the free section 1211 from interfering with the limiting pin 230 when the limiting pin 230 passes into or out of the limiting clamping hole 121, thereby affecting the disassembly and assembly efficiency of the load module 200 and the fuselage module 100.

[0062] Furthermore, in this embodiment, if Figure 5 As shown, the load module 200 further includes a mounting nut 240, and the limit pin 230 is screwed to the mounting nut 240 to be locked and connected to the load mounting member 220. In this way, the limit pin 230 is fixedly connected to the load mounting member 220, and the limit pin 230 cooperates with the limit clamping hole 121 to correspondingly realize the detachable connection between the load mounting member 220 and the load hanging member 120. Of course, in other embodiments, the limit pin can also be connected to the load mounting member by riveting or welding.

[0063] Further, in this embodiment, the mounting nut 240 is embedded in the load mounting member 220. Without loss of generality, in this embodiment, the edge portion of the load mounting member 220 is bonded to the second panel 210, and the middle main body portion is raised compared to the surface of the second panel 210, so that the main body portion is arranged away from the second panel 210. Further, a avoidance hole is provided in the middle of the main body portion to facilitate the installation of the load on the main body portion. The mounting nut 240 needs to be installed on the side of the load mounting member 220 away from the load hanging member 120. In order to improve the installation convenience of the limit pin 230, in this embodiment, the mounting nut 240 is embedded in the load mounting member 220. In this way, the limit pin 230 is screwed into the mounting nut 240, so that the limit pin 230 can be fixedly installed on the load mounting member 220, and the head 232 of the limit pin 230 will be located on the side close to the load hanging member 120, so that the limit pin 230 can penetrate into or out of the limit clamping hole 121. Optionally, the mounting nut 240 may be pre-embedded in the load mounting member 220 by bonding, welding or snap connection.

[0064] Furthermore, in this embodiment, a second protruding ring 235 is protruded outwardly from one end of the pin body 233 away from the head 232, and the second protruding ring 235 and the mounting nut 240 are respectively arranged on opposite sides of the load mounting member 220. In this embodiment, the load mounting member 220 is sandwiched between the mounting nut 240 and the second protruding ring 235 to improve the connection stability between the limit pin 230 and the load mounting member 220. In addition, during the process of the limit pin 230 being screwed into the mounting nut 240, the second protruding ring 235 can also play a positioning role to prevent the portion of the limit pin 230 screwed into the mounting nut 240 from being too long, thereby preventing the head 232 of the limit pin 230 from passing through the limit clamping hole 121.

[0065] Furthermore, in this embodiment, if Figure 2 As shown, the fuselage module 100 further includes a first connector 150 disposed on the load hanging member 120, such as Figure 3As shown, the load module 200 further includes a second connector 250 provided on the load mounting member 220, and the second connector 250 is used to be electrically connected to the load; when the stop pin 230 is stuck in the locking section 1212, the first connector 150 is in contact with the second connector 250; when the stop pin 230 is located in the free section 1211, the second connector 250 is separated from the first connector 150. It can be understood that the fuselage module 100 will be provided with a main control board, the first connector 150 is electrically connected to the main control board, and the second connector 250 is connected between the first connector 150 and the load, which is equivalent to the first connector 150 and the second connector 250 as an intermediate bridge, the purpose of which is to finally enable the load to be electrically connected and communicated with the main control board, so as to receive instructions issued by the main control board. In the present embodiment, when the fuselage module 100 and the payload module 200 are disassembled or installed, the first connector 150 of the fuselage module 100 and the second connector 250 of the payload module 200 can be disconnected or connected accordingly, and no additional actions are required on the first connector 150 and the second connector 250. That is, the disassembly and assembly of the first connector 150 and the second connector 250 will be carried out simultaneously with the disassembly and assembly of the first panel 110 and the second panel 210 and the disassembly and assembly of the load hanging component 120 and the load mounting component 220. In this way, the disassembly and assembly of the fuselage module 100 and the payload module 200 can be simpler and faster, so as to further improve the disassembly and assembly efficiency of the fuselage module 100 and the payload module 200.

[0066] Furthermore, in this embodiment, if Figure 2 As shown, the load hanging member 120 is provided with a first mounting seat 151, the first connector 150 is mounted on the first mounting seat 151, and the first mounting seat 151 is detachably connected to the load hanging member 120; Figure 3 As shown, the load mounting member 220 is provided with a second mounting seat 251, and the second connector 250 is mounted on the second mounting seat 251, and the second mounting seat 251 is detachably connected to the load mounting member 220. In this way, when different loads are replaced and different connectors need to be replaced synchronously, the first mounting seat 151 and the second mounting seat 251 are disassembled respectively, and the types of the first connector 150 and the second connector 250 can be replaced. Of course, in other embodiments, it is also possible that the first connector is detachably mounted on the first mounting seat; the second connector is detachably mounted on the second mounting seat, so that different types of connectors can be replaced on the same mounting seat.

[0067] The above descriptions are only optional embodiments of the present invention, and are not intended to limit the patent scope of the present invention. All equivalent structural changes made using the contents of the present invention's specification and drawings, or directly / indirectly applied in other related technical fields, are included in the patent protection scope of the present invention.

Claims

1. A drone, characterized in that: include: The fuselage module comprises a first panel and a load hanging member arranged inside the first panel, the load hanging member is provided with a limit clamping hole, the limit clamping hole comprises a free section and a locking section connected to each other, and the aperture of the limit clamping hole at the free section is larger than the aperture of the locking section; A load module, comprising a second panel and a load mounting member disposed inside the second panel, the load mounting member being used to mount a load, the load mounting member being provided with a limit pin, the limit pin being able to pass through the free section and be clamped into the locking section; and The locking module includes a first locking member and a second locking member that are detachably connected; the first locking member is connected to the first panel, the second locking member is connected to the second panel, and when the first locking member is connected to the second locking member, the limit pin is limited to the locking section to lock the load module with the fuselage module.

2. The drone according to claim 1, characterized in that: The first locking member is a locking screw, and the second locking member is a locking nut. The locking screw is arranged on the first panel, and the second panel is provided with a screw hole for the locking screw to pass through. The locking nut is connected to the side of the second panel away from the first panel and is locked to the locking screw.

3. The drone according to claim 2, characterized in that: The locking nut is a hand-tightening nut; And / or, a mounting angle code is provided on a side of the first panel, and the locking screw is installed on the mounting angle code.

4. The drone according to claim 1, wherein: The limiting pin is provided with a limiting ring groove, and the hole wall of the locking section is clamped in the limiting ring groove.

5. The drone according to claim 4, characterized in that: The load hanging part is provided with a retaining rib extending along the periphery of the free section to limit the hole wall of the free section from being stuck into the limiting ring groove; And / or, the limiting pin includes a head and a pin body connected to each other, and an end of the pin body close to the head is provided with a first convex ring protruding outwardly, and the limiting ring groove is limited between the first convex ring and the head.

6. The drone according to claim 1, wherein: The load module further includes a mounting nut, and the limiting pin is threadedly connected to the mounting nut to be locked and connected to the load mounting member.

7. The drone according to claim 6, characterized in that: The mounting nut is pre-buried on the load mounting member; And / or, the limit pin includes a head and a pin body connected to each other, and a second convex ring is protruding outward from one end of the pin body away from the head, and the second convex ring and the mounting nut are arranged on opposite sides of the load mounting member.

8. The drone according to claim 1, wherein: The first panel limits a mounting groove, and the second panel is adapted to cover the notch of the mounting groove to limit a receiving cavity between the first panel and the second panel, and the receiving cavity is used to accommodate the load hanging component, the load mounting component and the load.

9. The drone according to claim 8, characterized in that: The first panel also includes a reinforcing flange extending along the notch of the mounting slot, and the reinforcing flange is protruding toward the inside of the mounting slot.

10. The drone according to claim 9, characterized in that: The reinforcing flange includes two first flanges that are relatively protruding, and the opposite sides of the load hanging component are bonded to the two first flanges.

11. The drone according to claim 1, wherein: The load hanging component is also provided with a reinforcing plate, which is arranged close to the limit clamping hole and extends in a direction away from the load module.

12. The drone according to claim 11, characterized in that: The load hanging part is also provided with a connection hole arranged close to the limit clamping hole, and the reinforcing plate is provided with a connection groove; The reinforcing plate is inserted from the connecting hole, and the hole wall of the connecting hole is stuck in the connecting groove to be mortise-joined with the load hanging component.

13. The drone according to any one of claims 1 to 12, characterized in that: The fuselage module further comprises a first connector provided on the load hanging member, and the load module further comprises a second connector provided on the load mounting member, wherein the second connector is used for being electrically connected to the load; When the limiting pin is stuck in the locking section, the first connector contacts and is connected to the second connector; When the limiting pin is located in the free section, the second connector is separated from the first connector.

14. The drone according to claim 13, characterized in that: The load hanging component is provided with a first mounting seat, the first connector is mounted on the first mounting seat, and the first mounting seat is detachably connected to the load hanging component; and / or the first connector is detachably mounted on the first mounting seat; The load mounting member is provided with a second mounting seat, the second connector is mounted on the second mounting seat, and the second mounting seat is detachably connected to the load mounting member; And / or, the second connector can be detachably mounted on the second mounting seat.

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