The fuselage frame of a heavy-duty drone

Abstract

This utility model relates to the field of unmanned aerial vehicle (UAV) technology and discloses a fuselage frame for a heavy-duty UAV, including: a platform, a fuselage, and four arms. The platform is installed inside the fuselage, and the four arms are mounted on the fuselage. The fuselage includes two center plates, and two parallel connecting bodies are installed between the two center plates. The end of the platform is connected to the surface of the connecting bodies. Each center plate has a symmetrically arranged mounting part. The mounting part contains a first positioning component and a second positioning component for mounting the arms. A motor is installed at the end of each arm away from the mounting part. This heavy-duty UAV fuselage frame, by setting up mounting parts, a first positioning component, a second positioning component, and arms, allows the arms to be detachably mounted on the mounting parts via the first and second positioning component housings. This facilitates separation from the fuselage, allows for disassembly and stacking during transportation, saves transportation space, improves transportation efficiency, and facilitates transportation.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to the fuselage frame of a heavy-duty UAV. Background Technology

[0002] Unmanned aerial vehicles (UAVs), or URMs for short, are devices operated using radio remote control equipment and onboard program control devices, or operated autonomously, either completely or intermittently, by an onboard computer. UAVs have shown great application potential in civilian fields such as agricultural plant protection, logistics transportation, and disaster relief. In agricultural scenarios, UAVs need to carry large-capacity medicine boxes or heavy equipment for long-endurance operations; while in the civilian logistics field, they need to meet the stable transportation needs of large-load materials, such as building materials and emergency supplies.

[0003] The fixed arms and landing gear on the drone extend outwards, making the drone take up more space and inconvenient to transport. Utility Model Content

[0004] To address the shortcomings of existing technologies, this utility model provides a fuselage frame for a heavy-duty unmanned aerial vehicle (UAV), thus solving the problems mentioned in the background.

[0005] This utility model provides the following technical solution: a fuselage frame for a heavy-duty unmanned aerial vehicle, comprising: a platform, a fuselage, and four arms, wherein the platform is installed inside the fuselage, and the four arms are installed on the fuselage. The fuselage includes two center plates, and two parallel connecting bodies are installed between the two center plates. The end of the platform is connected to the surface of the connecting body. Each center plate has a mounting part symmetrically arranged. The mounting part has a first positioning component and a second positioning component for mounting the robot arm. A motor is installed at the end of the robot arm away from the mounting part. A propeller is installed on the output shaft of the motor. The center plate has a placement slot, and a battery is installed in the placement slot. The top of the center plate has a fixing component for limiting the battery. The bottom of both center plates is equipped with landing gear.

[0006] Preferably, the first positioning component includes a fixing member and a bracket disposed on the inner wall of the mounting part. The top of the mounting part is provided with a movable groove, and the inner wall of the movable groove is connected to the surface of the fixing member. The inner wall of the fixing member is provided with a locking block. The surface of the arm is provided with a locking groove, and the inner wall of the locking groove is connected to the surface of the locking block. Both sides of the mounting part are provided with latches, and the hooks of the latches are installed on the surface of the fixing member.

[0007] Preferably, the second positioning component includes a positioning element and two limiting seats disposed on the inner wall of the mounting part. The mounting part has a mounting groove on its side. The positioning element is connected to the inner wall of the mounting groove. A fixing bolt is disposed between the positioning element and the limiting seats. The inner walls of the positioning element and the inner walls of the limiting seats are both connected to the surface of the machine arm.

[0008] Preferably, the fixing component includes a mounting shell, and the inner wall of the mounting shell is respectively provided with a spring and a limiting block. One end of the spring is connected to the inner wall of the mounting shell, and the other end of the spring is connected to the surface of the limiting block.

[0009] Preferably, the inner wall of the mounting shell is symmetrically provided with guide seats, the surface of the limiting block is connected with guide blocks, and the two ends of the guide blocks are slidably connected to the inner walls of the two guide seats respectively.

[0010] Preferably, the landing gear surface is symmetrically provided with mounting seats and fixing blocks, the fixing blocks are mounted on the inner wall of the mounting seats by mounting bolts, and the mounting seats are mounted on the bottom of the center plate.

[0011] Preferably, an antenna is mounted on the top of the mounting portion.

[0012] Preferably, the motor is equipped with an electronic speed controller.

[0013] Compared with the prior art, the present invention has the following beneficial effects: 1. The fuselage frame of the heavy-duty UAV is provided with an installation part, a first positioning component, a second positioning component, and an arm. The arm is detachably installed on the installation part through the first positioning component and the second positioning component shell, which facilitates separation from the fuselage. It can be disassembled and stacked during transportation, saving transportation space, improving transportation efficiency, and facilitating transportation.

[0014] 2. The fuselage frame of this heavy-duty drone has a fixed component. When installing the battery, the limiting block is pushed into the inside of the mounting shell. After the battery is placed into the placement slot, the limiting block is released, and the spring pushes the limiting block above the battery to limit the battery position. Attached Figure Description

[0015] Figure 1 This is a three-dimensional structural diagram of the present invention; Figure 2 This is a schematic diagram of the structure at the landing gear position of this utility model; Figure 3 This utility model Figure 2 Enlarged structural diagram at point A in the middle; Figure 4 This is a partially enlarged side section view of the first positioning component of this utility model. Figure 5This is a partially enlarged structural diagram of the second positioning component of this utility model; Figure 6 This is a schematic diagram of the platform structure of this utility model; Figure 7 This is a schematic diagram of the central plate and mounting part of this utility model; Figure 8 This is a schematic diagram of the arm structure of this utility model; Figure 9 This is a schematic diagram of the fastener structure of this utility model; Figure 10 This is a schematic diagram of the positioning component structure of this utility model; Figure 11 This is an exploded structural diagram of the fixing component of this utility model.

[0016] In the diagram: 1. Platform; 2. Fuselage; 201. Center plate; 202. Connector; 3. Arm; 4. Mounting section; 5. First positioning assembly; 51. Fixing component; 52. Bracket; 53. Locking block; 54. Hook and latch; 55. Hook and latch; 6. Second positioning assembly; 61. Positioning component; 62. Limiting seat plate; 7. Motor; 8. Propeller; 9. Battery; 10. Fixing assembly; 101. Mounting shell; 102. Spring; 103. Limiting block; 11. Landing gear; 12. Movable slot; 13. Slot; 14. Antenna; 15. Electronic speed controller; 16. Mounting slot; 17. Fixing bolt; 18. Guide seat; 19. Guide block; 20. Mounting seat; 21. Fixing block; 22. Mounting bolt. Detailed Implementation

[0017] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0018] Please see Figure 1-11The fuselage frame of the heavy-duty drone includes: a platform 1, a fuselage 2, and four arms 3. The platform 1 is installed inside the fuselage 2, and the four arms 3 are installed on the fuselage 2. The fuselage 2 includes two center plates 201, and two parallel connecting bodies 202 are installed between the two center plates 201. The end of the platform 1 is connected to the surface of the connecting body 202. Each center plate 201 has a mounting part 4 symmetrically arranged. An antenna 14 is installed on the top of the mounting part 4. The mounting part 4 has a first positioning component 5 and a second positioning component 6 for mounting the arms 3. A motor 7 is installed at the end of the arm 3 away from the mounting part 4. A propeller 8 is installed on the output shaft of the motor 7. An electronic speed controller 15 is installed on the motor 7. The center plate 201 has a placement slot, and a battery 9 is installed in the placement slot. A fixing component 10 for limiting the battery 9 is provided on the top of the center plate 201. Landing gears 11 are provided at the bottom of both center plates 201.

[0019] The first positioning component 5 includes a fixing member 51 and a bracket 52 disposed on the inner wall of the mounting part 4. The top of the mounting part 4 is provided with a movable groove 12, and the inner wall of the movable groove 12 is connected to the surface of the fixing member 51. The inner wall of the fixing member 51 is provided with a locking block 53. The surface of the arm 3 is provided with a locking groove 13, and the inner wall of the locking groove 13 is connected to the surface of the locking block 53. Both sides of the mounting part 4 are provided with a latch lock 54, and the hook 55 of the latch lock 54 is installed on the surface of the fixing member 51. The second positioning component 6 includes a positioning member 61 and two limiting seats 62 disposed on the inner wall of the mounting part 4. The side of the mounting part 4 is provided with a mounting groove 16. The positioning member 61 is connected to the inner wall of the mounting groove 16. A fixing bolt 17 is provided between the positioning member 61 and the limiting seats 62. The inner walls of the positioning member 61 and the limiting seats 62 are both connected to the surface of the arm 3.

[0020] The fixing component 10 includes a mounting shell 101. A spring 102 and a limiting block 103 are respectively provided on the inner wall of the mounting shell 101. One end of the spring 102 is connected to the inner wall of the mounting shell 101, and the other end of the spring 102 is connected to the surface of the limiting block 103. When installing the battery 9, the limiting block 103 is pushed into the interior of the mounting shell 101. After the battery 9 is placed into the placement slot, the limiting block 103 is released. The spring 102 pushes the limiting block 103 above the battery 9 to limit the position of the battery 9. Guide seats 18 are symmetrically provided on the inner wall of the mounting shell 101. Guide blocks 19 are connected to the surface of the limiting block 103. The two ends of the guide blocks 19 are slidably connected to the inner walls of the two guide seats 18 respectively. The guide blocks 19 slide on the inner walls of the guide seats 18 to guide the limiting block 103, so that the limiting block 103 moves stably.

[0021] The landing gear 11 has symmetrical mounting bases 20 and fixing blocks 21 on its surface. The fixing blocks 21 are mounted on the inner wall of the mounting base 20 by mounting bolts 22. The mounting base 20 is mounted on the bottom of the center plate 201.

[0022] During transportation, the arm 3 is removed from the mounting part 4 of the center plate 201. The end of the arm 3 with the slot 13 is inserted into the mounting part 4, and the surface of the arm 3 is in contact with the inner wall of the limiting seat 62 and the bracket 52. The fixing piece 51 is inserted into the movable slot 12, and the locking block 53 on the fixing piece 51 aligns with the slot 13. The fixing is completed by locking the buckle lock 54. The positioning piece 61 is inserted into the mounting slot 16, and the limiting seat 62 and the positioning piece 61 are connected by the fixing bolt 17 to further fix the arm 3. The arm 3 is easy to install and easy to separate from the body 2. It can be disassembled and stacked during transportation, saving transportation space, improving transportation efficiency, and facilitating transportation.

[0023] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A fuselage frame of a payload drone, characterized in that, include: The platform (1), the fuselage (2), and four arms (3) are provided, wherein the platform (1) is installed inside the fuselage (2) and the four arms (3) are installed on the fuselage (2); The fuselage (2) includes two center plates (201), and two parallel connecting bodies (202) are installed between the two center plates (201). The end of the platform (1) is connected to the surface of the connecting body (202). Each center plate (201) is symmetrically provided with a mounting part (4). The mounting part (4) is provided with a first positioning component (5) and a second positioning component (6) for mounting the arm (3). A motor (7) is installed at the end of the arm (3) away from the mounting part (4). A propeller (8) is installed on the output shaft of the motor (7). The center plate (201) is provided with a placement slot, and a battery (9) is installed in the placement slot. A fixing component (10) for limiting the battery (9) is provided on the top of the center plate (201). A landing gear (11) is provided at the bottom of both center plates (201).

2. The frame of the unmanned aerial vehicle according to claim 1, wherein, The first positioning component (5) includes a fixing member (51) and a bracket (52) disposed on the inner wall of the mounting part (4). The top of the mounting part (4) is provided with a movable groove (12), and the inner wall of the movable groove (12) is connected to the surface of the fixing member (51). The inner wall of the fixing member (51) is provided with a locking block (53). The surface of the arm (3) is provided with a locking groove (13), and the inner wall of the locking groove (13) is connected to the surface of the locking block (53). Both sides of the mounting part (4) are provided with a latch lock (54), and the hook (55) of the latch lock (54) is installed on the surface of the fixing member (51).

3. The frame of claim 1, wherein, The second positioning component (6) includes a positioning element (61) and two limiting seats (62) disposed on the inner wall of the mounting part (4). The mounting part (4) has a mounting groove (16) on its side. The positioning element (61) is connected to the inner wall of the mounting groove (16). A fixing bolt (17) is provided between the positioning element (61) and the limiting seats (62). The inner walls of the positioning element (61) and the limiting seats (62) are both connected to the surface of the arm (3).

4. The frame of claim 1, wherein, The fixing component (10) includes a mounting shell (101), and the inner wall of the mounting shell (101) is provided with a spring (102) and a limiting block (103). One end of the spring (102) is connected to the inner wall of the mounting shell (101), and the other end of the spring (102) is connected to the surface of the limiting block (103).

5. The frame of the body of the payload drone according to claim 4, characterized in that, The inner wall of the mounting shell (101) is symmetrically provided with guide seats (18), and the surface of the limiting block (103) is connected with guide blocks (19). The two ends of the guide blocks (19) are slidably connected to the inner walls of the two guide seats (18).

6. The frame of the unmanned aerial vehicle according to claim 1, wherein, The landing gear (11) is symmetrically provided with mounting bases (20) and fixing blocks (21). The fixing blocks (21) are installed on the inner wall of the mounting base (20) by mounting bolts (22). The mounting base (20) is installed on the bottom of the center plate (201).

7. The frame of claim 1, wherein, The top of the mounting part (4) is provided with an antenna (14).

8. The frame of claim 1, wherein, An electronic speed regulator (15) is mounted on the motor (7).

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