Portable unmanned aerial vehicle

Abstract

The utility model discloses a portable unmanned aerial vehicle. The unmanned aerial vehicle comprises an unmanned aerial vehicle main body and an aileron arm, the outer wall of the unmanned aerial vehicle main body is fixedly connected with a main wing arm, one end of the main wing arm is fixedly provided with a power-on seat, one end of the main wing arm is provided with a stress insertion hole, the upper surface of the main wing arm is provided with a limiting insertion hole, and one end of the aileron arm is fixedly provided with a power-on plug. The auxiliary wing arms are inserted into the main wing arms, so that the electrifying plugs can be inserted into the electrifying seats to be electrified for use, and meanwhile, the stress strips are inserted into the stress insertion holes to be butted and stressed, so that the weight of an unmanned aerial vehicle main body can be borne during flight, and the device can form a detachable structure; after the unmanned aerial vehicle main body falls by mistake and one end of the aileron arm is damaged, the replaced aileron arm can be conveniently detached for use, and the whole shell or the wing arm does not need to be replaced for maintenance, so that the use and maintenance cost of the unmanned aerial vehicle is greatly reduced, and convenience is provided for use and maintenance of the unmanned aerial vehicle.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a lightweight unmanned aerial vehicle. Background Technique

[0002] An unmanned aerial vehicle, abbreviated as "UAV", is an unpiloted aircraft controlled by a radio remote control device and a self - contained program control device. From a technical perspective, it can be divided into: unmanned fixed - wing aircraft, unmanned vertical take - off and landing aircraft, unmanned airship, unmanned helicopter, unmanned multi - rotor aircraft, unmanned parafoil aircraft, etc. In terms of application fields, for civilian use, the industrial application of UAVs is the real demand. At present, its applications in fields such as aerial photography, agriculture, plant protection, micro - self - shooting, and express delivery have greatly expanded the uses of UAVs themselves. Developed countries are also actively expanding industrial applications and developing UAV technologies.

[0003] With the development of UAV technology, the manufacturing cost of UAVs has decreased, enabling many UAVs to be targeted at the civilian market. Such UAVs are widely loved for their low price, high performance, light weight, and easy operation. At present, the wing arms of UAVs on the market are divided into fixed - type or foldable types. Accidents often occur where the operator makes a mistake or during the initial learning stage, causing the UAV to crash. When it falls from a high altitude, the damaged part is mostly the wing arm, resulting in the wing arm being broken and unable to be used. Subsequent repairs require replacing the entire outer shell or the entire wing arm, increasing the use, repair, and maintenance costs, and making the use, repair, and maintenance of UAVs relatively inconvenient. Content of the Utility Model

[0004] The purpose of the utility model is to provide a lightweight unmanned aerial vehicle to solve the problems raised in the above - mentioned background technique.

[0005] To achieve the above purpose, the utility model provides the following technical solutions:

[0006] A lightweight unmanned aerial vehicle, including a UAV main body and auxiliary wing arms. The outer wall of the UAV main body is fixedly connected with main wing arms. One end of the main wing arm is fixedly installed with a power - on socket, and a force - receiving socket is opened at one end of the main wing arm. A limit socket is opened on the upper surface of the main wing arm. One end of the auxiliary wing arm is fixedly installed with a power - on plug, and one end of the power - on plug is inserted into the power - on socket. One end of the auxiliary wing arm is inserted with a force - receiving bar, and one end of the force - receiving bar is inserted into the force - receiving socket. A fixing hole is opened on the upper surface of the force - receiving bar, and a positioning pin is inserted into the inner walls of the limit socket and the fixing hole.

[0007] Preferably, a limit groove is opened on the inner wall of the limit socket, and a limit convex block is fixedly connected to the top of the positioning pin, and the limit convex block is located in the limit groove.

[0008] Preferably, one end of the aileron arm is fixedly connected with an assembly seat, a brushless motor is inserted into the interior of the assembly seat, a threaded gland is inserted on the outer wall of the rotating shaft of the brushless motor, and the bottom end of the threaded gland is threadedly connected to the top of the assembly seat.

[0009] Preferably, a power-on head is arranged at the bottom of the assembly seat, and a power-on hole at the bottom of the brushless motor is inserted on the power-on head.

[0010] Preferably, a rotating head is fixedly welded on the upper surface of the positioning pin at the position of the limiting lug, a notch is formed at the top of one end of the limiting groove, and the limiting lug and the notch have the same shape and size.

[0011] Preferably, two stress jacks are formed at one end of the main wing arm, two stress bars are inserted at one end of the aileron arm, and the two stress bars are inserted into the stress jacks at corresponding positions. The stress bars are made of aluminum alloy bars.

[0012] Preferably, one end of the power-on seat is connected to the control board of the UAV body by a data line, and the power-on plug and the power-on head are connected by a data line.

[0013] Preferably, a support foot is fixedly connected to the bottom of the assembly seat, and the bottom end of the support foot is lower than the lower surface of the UAV body.

[0014] Compared with the prior art, the beneficial effects of the utility model are as follows:

[0015] (1) By inserting the aileron arm on the main wing arm, the power-on plug can be inserted into the power-on seat for power-on use. At the same time, the stress bars are inserted into the stress jacks for docking and stress, so as to ensure that the weight of the UAV body can be borne during flight, so that the device can form a detachable structure. After the aileron arm at one end of the UAV body falls and is damaged during an accident, it is convenient to remove and replace the good aileron arm, and there is no need to replace the entire shell or wing arm for maintenance, which greatly reduces the use and maintenance cost of the UAV and provides convenience for the use, maintenance and repair of the UAV.

[0016] (2) By inserting the positioning pin to limit the problem of loosening of the stress bars, after the positioning pin is inserted in place, the positioning pin can be rotated to move the limiting lug on the outer wall to the innermost end of the limiting groove. Since the top of the limiting lug is blocked, the positioning pin is limited and cannot be separated from the limiting jack, which can make the positioning pin stably inserted to limit the stress bars under the condition of the flight vibration of the UAV body, so as to improve the stability and firmness of the aileron arm after being inserted and assembled, so as to ensure the stability and safety during long-term flight.

[0017] (3) By inserting the brushless motor into the assembly base and threadedly connecting the threaded gland on the brushless motor to the assembly base, after the threaded gland is threadedly connected in place, the brushless motor below can be tightly fixed for use. This assembly method can be quickly disassembled and assembled. When the aileron arm is damaged, the brushless motor can be removed and assembled on a new aileron arm for use, so as to improve the utilization rate of the original parts, reduce the maintenance cost, and the structure that is convenient for disassembly and assembly can be used to replace brushless motors of different models according to personal needs, which is convenient for users to modify and improve the use experience. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required to be used in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0019] Figure 1 is a schematic diagram of the overall structure of the device of the lightweight unmanned aerial vehicle according to an embodiment of the present invention;

[0020] Figure 2 is a schematic diagram of the connection between the main wing arm and the aileron arm according to an embodiment of the present invention;

[0021] Figure 3 is a schematic diagram of the force receiving socket and the power-on seat according to an embodiment of the present invention;

[0022] Figure 4 is a schematic diagram of the force receiving bar and the power-on plug according to an embodiment of the present invention;

[0023] Figure 5 is an exploded view of the positioning pin and the limit socket according to an embodiment of the present invention;

[0024] Figure 6 is a schematic diagram of the connection between the brushless motor and the assembly base according to an embodiment of the present invention.

[0025] In the figure: 1, unmanned aerial vehicle body; 2, main wing arm; 3, power-on seat; 4, force receiving socket; 5, limit socket; 6, limit groove; 7, aileron arm; 8, power-on plug; 9, force receiving bar; 10, fixing hole; 11, positioning pin; 12, limit bump; 13, assembly base; 14, power-on head; 15, brushless motor; 16, threaded gland; 17, support foot. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0026] The following will clearly and completely describe the technical solutions in the embodiments of the present utility model in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0027] The following will further elaborate on the present utility model in conjunction with the attached Figure 1-6 to provide a more detailed description of the present utility model.

[0028] Embodiment 1

[0029] Please refer to Figures 1 to 6 , an embodiment provided by the present utility model: a lightweight unmanned aerial vehicle, including an unmanned aerial vehicle main body 1 and an aileron arm 7. An outer wall of the unmanned aerial vehicle main body 1 is fixedly connected with a main wing arm 2. One end of the main wing arm 2 is fixedly installed with a power supply socket 3. One end of the main wing arm 2 is provided with a force receiving socket 4. A limiting socket 5 is provided on an upper surface of the main wing arm 2. One end of the aileron arm 7 is fixedly installed with a power supply plug 8. One end of the power supply plug 8 is inserted into the power supply socket 3. One end of the aileron arm 7 is inserted with a force receiving bar 9. One end of the force receiving bar 9 is inserted into the force receiving socket 4. A fixing hole 10 is provided on an upper surface of the force receiving bar 9. A positioning pin 11 is inserted into inner walls of the limiting socket 5 and the fixing hole 10. By inserting the aileron arm 7 onto the main wing arm 2, the power supply plug 8 can be inserted into the power supply socket 3 for power-on use. At the same time, the force receiving bar 9 is inserted into the force receiving socket 4 for docking and force receiving, and the positioning pin 11 is inserted into the fixing hole 10 for limiting, so as to ensure that the weight of the unmanned aerial vehicle main body 1 can be borne during flight, enabling the device to form a detachable structure. After the end of the aileron arm 7 is damaged when the unmanned aerial vehicle main body 1 accidentally falls, it is convenient to remove and replace the damaged aileron arm 7, without the need to replace the entire housing or wing arm for repair, greatly reducing the use and repair costs of the unmanned aerial vehicle and providing convenience for the use, repair and maintenance of the unmanned aerial vehicle.

[0030] Embodiment 2

[0031] Please refer to Figures 1 to 6 , a limiting groove 6 is provided on an inner wall of the limiting socket 5. A limiting convex block 12 is fixedly connected to a top of the positioning pin 11. The limiting convex block 12 is located in the limiting groove 6. By inserting the positioning pin 11, the problem of loosening of the force receiving bar 9 is restricted. After the positioning pin 11 is inserted in place, the positioning pin 11 can be rotated to move the limiting convex block 12 on the outer wall to the innermost end of the limiting groove 6. Since the top of the limiting convex block 12 is blocked, the positioning pin 11 is limited and cannot be separated from the limiting socket 5, enabling the positioning pin 11 to be stably inserted to restrict the force receiving bar 9 under the flight shaking of the unmanned aerial vehicle main body 1, so as to improve the stability and firmness of the assembled aileron arm 7, and to ensure the stability and safety during long-term flight;

[0032] One end of the aileron arm 7 is fixedly connected with an assembly seat 13. A brushless motor 15 is inserted into the interior of the assembly seat 13. A threaded gland 16 is inserted on the outer wall of the rotating shaft of the brushless motor 15. The bottom end of the threaded gland 16 is threadedly connected to the top of the assembly seat 13. By inserting the brushless motor 15 into the assembly seat 13 and threadedly connecting the threaded gland 16 on the brushless motor 15 to the assembly seat 13, after the threaded gland 16 is threadedly connected in place, the lower brushless motor 15 can be tightly fixed for use. This assembly method can be quickly disassembled and assembled. When the aileron arm 7 is damaged, the brushless motor 15 can be removed and assembled on a new aileron arm 7 for use, so as to improve the utilization rate of components and reduce the maintenance cost. Moreover, the structure that is convenient for disassembly and assembly can be used to replace brushless motors 15 of different models according to one's own needs, which is convenient for users to modify and improve the use experience. An energizing head 14 is arranged at the bottom of the assembly seat 13. There is an energizing hole at the bottom of the brushless motor 15 inserted on the energizing head 14. By aligning the brushless motor 15 and inserting it into the assembly seat 13, the energizing hole of itself can be aligned with the energizing head 14 for insertion to form an electrical connection for energization use, simplifying the energizing connection method, replacing the existing connecting wire welding technology, and improving the convenience and flexibility of the device use.

[0033] Embodiment 3

[0034] Please refer to Figures 1 to 6 , a rotating head is fixedly welded on the upper surface of the positioning pin 11 at the position of the limiting convex block 12. A notch is opened at the top of one end of the limiting groove 6. The limiting convex block 12 has the same shape and size as the notch. By setting the notch, the limiting convex block 12 can be aligned with the notch and placed down to ensure that the positioning pin 11 can be smoothly inserted into the limiting jack 5. At the same time, after insertion, the rotating head can be used to push the positioning pin 11 to rotate, so that the limiting convex block 12 rotates to the other end in the limiting groove 6 to abut and limit. Two groups of force-receiving jacks 4 are opened at one end of the main wing arm 2. Two groups of force-receiving bars 9 are inserted into one end of the aileron arm 7. The two groups of force-receiving bars 9 are inserted into the force-receiving jacks 4 at corresponding positions. The force-receiving bars 9 are aluminum alloy bars. By setting the upper and lower two groups of force-receiving jacks 4 and the force-receiving bars 9 for insertion and fixation, the upper and lower surfaces of the main wing arm 2 and the aileron arm 7 can be supported, improving the force-bearing strength at the upper and lower ends of the connection, so as to ensure that the force in the direction can be withstood and improving the stability and safety of the UAV body 1 during flight. At the same time, by embedding the aluminum alloy bars in the aileron arm 7, the high-strength property of the aluminum alloy bars can be used to improve the bearing capacity, and the aluminum alloy material is lighter, which can reduce the weight of the UAV body 1 while ensuring the strength;

[0035] One end of the power-on base 3 is connected to the control board of the drone body 1 by a data cable. The power-on plug 8 and the power-on head 14 are connected by a data cable. By connecting the power-on base 3, the power-on plug 8 and the power-on head 14 through the data cable and cooperating with the plug-in power-on method, the brushless motor 15 can receive the power and electrical signals output by the control board of the drone body 1 and rotate for flight. The bottom of the assembly base 13 is fixedly connected with a support foot 17. The bottom end of the support foot 17 is lower than the lower surface of the drone body 1. By fixedly connecting the support foot 17 to the bottom of the assembly base 13, the drone body 1 can be supported, so that the drone body 1 does not contact the ground from the bottom. In case of water accumulation on the road surface or complex road conditions on rainy days, it can support and separate from the ground to protect the drone body 1 from damage.

[0036] Working principle: When replacing, insert the aileron arm 7 into one end of the main wing arm 2. While inserting, insert the power-on plug 8 into the power-on base 3, and insert the force-bearing bar 9 into the force-bearing jack 4 to bear. After inserting in place, insert the positioning pin 11 into the limit jack 5, and align the limit convex block 12 with the notch in the limit groove 6. Then rotate the positioning pin 11 to make the limit convex block 12 enter the limit groove 6 for limiting, thus completing the limiting of the force-bearing bar 9. At this time, the replacement of the new aileron arm 7 is completed. Insert the brushless motor 15 into the assembly base 13, and thread the thread cover 16 on the brushless motor 15 onto the assembly base 13. After the thread cover 16 is threaded in place, the lower brushless motor 15 can be firmly fixed for use.

[0037] For those skilled in the art, it is obvious that the present invention is not limited to the details of the above exemplary embodiments, and can be implemented in other specific forms without departing from the spirit or basic characteristics of the present invention.

Claims

1. A lightweight drone, comprising a drone body (1) and aileron arms (7), characterized in that: The outer wall of the drone body (1) is fixedly connected with a main wing arm (2). One end of the main wing arm (2) is fixedly installed with a power-on seat (3). One end of the main wing arm (2) is provided with a force-receiving socket (4). The upper surface of the main wing arm (2) is provided with a limit socket (5). One end of the auxiliary wing arm (7) is fixedly installed with a power-on plug (8). One end of the power-on plug (8) is inserted into the power-on seat (3). One end of the auxiliary wing arm (7) is inserted with a force-receiving bar (9). One end of the force-receiving bar (9) is inserted into the force-receiving socket (4). The upper surface of the force-receiving bar (9) is provided with a fixing hole (10). A positioning pin (11) is inserted into the inner walls of the limit socket (5) and the fixing hole (10).

2. The lightweight drone according to claim 1, wherein: A limit groove (6) is provided in the inner wall of the limit socket (5). The top of the positioning pin (11) is fixedly connected with a limit convex block (12). The limit convex block (12) is located in the limit groove (6).

3. A portable drone according to claim 1, characterized in that: One end of the auxiliary wing arm (7) is fixedly connected with an assembly seat (13). A brushless motor (15) is inserted into the interior of the assembly seat (13). The outer wall of the rotating shaft of the brushless motor (15) is inserted with a threaded gland (16). The bottom end of the threaded gland (16) is threadedly connected to the top of the assembly seat (13).

4. A portable unmanned aerial vehicle according to claim 3, characterized in that: A power-on head (14) is arranged at the bottom of the assembly seat (13). The bottom of the brushless motor (15) has a power-on hole inserted on the power-on head (14).

5. The lightweight drone according to claim 2, wherein: A rotating head is fixedly welded on the upper surface of the positioning pin (11) at the position of the limit convex block (12). A notch is provided at the top of one end of the limit groove (6). The limit convex block (12) has the same shape and size as the notch.

6. The portable unmanned aerial vehicle according to claim 1, wherein: Two groups of force-receiving sockets (4) are provided at one end of the main wing arm (2). Two groups of force-receiving bars (9) are inserted into one end of the auxiliary wing arm (7). The two groups of force-receiving bars (9) are inserted into the force-receiving sockets (4) at corresponding positions. The force-receiving bars (9) are made of aluminum alloy bars.

7. A portable drone according to claim 4, characterized in that: One end of the power-on seat (3) has a data line connected to the control board of the drone body (1). A data line is connected between the power-on plug (8) and the power-on head (14).

8. The lightweight drone according to claim 3, characterized in that: A support foot (17) is fixedly connected to the bottom of the assembly seat (13). The bottom end of the support foot (17) is lower than the lower surface of the drone body (1).

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