Quick disassembly and assembly structure of vertical take-off and landing unmanned aerial vehicle arm

Abstract

The utility model relates to an unmanned aerial vehicle arm quick disassembly and assembly structure, belongs to the technical field of unmanned aerial vehicles, and particularly relates to a vertical take-off and landing unmanned aerial vehicle arm quick disassembly and assembly structure which comprises a vehicle body, four vehicle arms are movably connected to the vehicle body in an inserted mode, and four motors are fixedly connected to the four vehicle arms respectively. Four wings are arranged on the four motors respectively, the unmanned aerial vehicle further comprises a first connecting assembly, and the first connecting assembly comprises a connecting shell, an elastic clamping block, a button, an electromagnet, an iron block and a spring; according to the unmanned aerial vehicle arm, the first connecting assembly is matched with the connecting shell, the elastic clamping block, the button, the electromagnet, the iron block and the spring, so that the iron block abuts against the elastic clamping block in the flying process, the elastic clamping block cannot move downwards, the stability of the unmanned aerial vehicle arm in the flying process is ensured, and the second connecting assembly is matched with the bolt through the groove, the rotating cover, the fixed block, the sliding block, the limiting hole and the bolt; and the sliding block is pushed by the rotating cover to be embedded into the groove, and the effect of reinforcing the machine arm is achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a quick disassembly and assembly structure of a machine arm of a vertical take-off and landing unmanned aerial vehicle. Background Art

[0002] Currently, drones on the market generally use multiple arm structures. In order to facilitate the quick installation of the arms, the industry generally adopts a plug-in structure.

[0003] The Chinese patent with the announcement number CN220616221U discloses a structure for quick disassembly and assembly of the arm of a drone. It includes: a fuselage and an arm, a cavity is provided inside the fuselage, a plug hole matching the arm is provided on the side of the fuselage, a main electrical plug end arranged opposite to the plug hole is provided in the cavity, the front end of the arm is a connection end, the connection end is connected to a secondary electrical plug end matching the main electrical plug end, a side of the connection end is provided with a barbed buckle and an elastic sheet connected to the buckle, one end of the elastic sheet is located outside the plug hole, the side wall of the plug hole is provided with a clamping hole matching the buckle or the plug hole is provided with a connecting sleeve clamped with the buckle, and the connecting sleeve is sleeved with the connecting end. The patent sets a buckle on the arm and sets a clamping hole or a connecting sleeve in the plug hole of the fuselage, so that the arm can be clamped at the same time as it is plugged in, and the arm and the fuselage are easy to disassemble and assemble.

[0004] In the above technical solution, the device only fixes the arm through the cooperation of the card block and the buckle, and squeezes the pressing block to take out the arm. Since drones are mostly used at high altitudes, rapid ascent and descent can easily cause the pressing block to move, resulting in the risk of the arm falling off during flight.

[0005] Based on this, the utility model proposes a quick disassembly and assembly structure of a vertical take-off and landing UAV arm. Utility Model Content

[0006] In order to solve the above technical problems, the utility model proposes a quick disassembly and assembly structure for the arm of a vertical take-off and landing UAV, which can use a first connecting component to use an iron block to support the elastic block during flight to prevent it from moving downward, and reinforce the arm through a second connecting component to ensure that the device is more stable during use.

[0007] The technical solution for achieving the purpose of the utility model is: a quick disassembly and assembly structure of the arms of a vertical take-off and landing unmanned aerial vehicle, including a fuselage, on which four arms are movably plugged, and four motors are fixedly connected to the four arms, respectively, and four wings are respectively arranged on the four motors, and a first connecting component is arranged on the fuselage, and the first connecting component includes a connecting shell, an elastic block, a button, an electromagnet, an iron block and a spring, the four connecting shells are fixedly connected to the fuselage, the four arms are respectively slidably connected to the four connecting shells, the four elastic blocks are respectively fixedly connected to the four arms, the four buttons are respectively fixedly connected to the four elastic blocks, the four electromagnets are respectively fixedly connected to the four connecting shells, the four iron blocks are respectively slidably connected to the four connecting shells, and the two ends of the multiple springs are respectively fixedly connected to the four iron blocks and the four connecting shells, and a second connecting component is arranged on the fuselage.

[0008] Preferably, the first connecting assembly further comprises supporting columns and through holes, the two ends of the four supporting columns are respectively fixedly connected to the four machine arms and the four elastic blocks, and the four through holes are respectively opened on the four connecting shells.

[0009] Preferably, a power supply is provided in the body, the four motors are electrically connected to the power supply, and the four electromagnets are electrically connected to the power supply.

[0010] Preferably, the second connecting component comprises a groove and a rotating cover, four of the grooves are respectively opened on four machine arms, and the rotating cover is rotatably connected to the machine body.

[0011] Preferably, the second connecting assembly further comprises a fixed block and a sliding block, the four fixed blocks are fixedly connected to the rotating cover, the four sliding blocks are respectively slidably connected to the body and the four grooves, and the four fixed blocks are respectively slidably connected to the four sliding blocks.

[0012] Preferably, the second connecting component further comprises a limiting hole and a latch, the limiting hole is formed on the body, and the latch is slidably connected to the rotating cover.

[0013] Compared with the prior art, the present invention has the following significant advantages:

[0014] First: In the utility model, the first connecting assembly cooperates with the connecting shell, the elastic block, the button, the electromagnet, the iron block and the spring, so that during flight, the iron block presses against the elastic block, preventing it from moving downward, thereby ensuring the stability of the aircraft arm during flight;

[0015] Second: In the utility model, the second connecting component cooperates with the groove, the rotating cover, the fixed block, the slider, the limiting hole and the latch, and the rotating cover is rotated, and the slider is pushed into the groove by the rotating cover, which has a reinforcement effect on the machine arm. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The present utility model will be further explained below in conjunction with the accompanying drawings and embodiments:

[0017] Figure 1 is a three-dimensional structural schematic diagram of the present utility model;

[0018] Figure 2 is an internal structural sectional view of the first connection component in the present utility model;

[0019] Figure 3 is an internal three-dimensional structural schematic diagram of the fuselage in the present utility model;

[0020] Figure 4 is a three-dimensional structural schematic diagram of the second connection component in the present utility model.

[0021] Explanation of reference numerals in the drawings:

[0022] 1. Fuselage; 2. Arm; 3. Motor; 4. Wing; 5. First connection component; 51. Connection shell; 52. Support column; 53. Through hole; 54. Elastic clamping block; 55. Button; 56. Electromagnet; 57. Iron block; 58. Spring; 6. Second connection component; 61. Groove; 62. Rotating cover; 63. Fixed block; 64. Slide block; 65. Limiting hole; 66. Plug; 7. Power supply. Specific embodiments

[0023] The present utility model will be described in detail below. The technical solutions in the embodiments of the present utility model are clearly and completely described. 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.

[0024] The present utility model provides a quick disassembly and assembly structure for the arm of a vertical takeoff and landing unmanned aerial vehicle through improvement. The technical solution of the present utility model is as follows:

[0025] As Figures 1 - 4As shown in the figure, a quick-disassembly and assembly structure for the arms of a vertical takeoff and landing drone includes a fuselage 1. Four arms 2 are movably inserted into the fuselage 1. The four arms 2 are distributed in a circular array with the center of the rotating cover 62 as the center. Four motors 3 are respectively fixedly connected to the four arms 2, and four wings 4 are respectively arranged on the four motors 3. A first connection assembly 5 is arranged on the fuselage 1. The first connection assembly 5 includes a connection shell 51, an elastic block 54, a button 55, an electromagnet 56, an iron block 57 and a spring 58. The four connection shells 51 are fixedly connected to the fuselage 1. The four arms 2 are respectively slidably connected to the four connection shells 51. One end of the four elastic blocks 54 away from the fuselage 1 is respectively fixedly connected to the four arms 2. The four buttons 55 are respectively fixedly connected to the four elastic blocks 54. The four electromagnets 56 are respectively fixedly connected to the four connection shells 51. The four iron blocks 57 are respectively slidably connected to the four connection shells 51. The top of the iron block 57 is slightly lower than the bottom of the elastic block 54. The two ends of multiple springs 58 are respectively fixedly connected to the four iron blocks 57 and the four connection shells 51. The springs 58 are distributed in a linear array on the iron block 57. A second connection assembly 6 is arranged on the fuselage 1.

[0026] Further, as Figure 2 shown, the first connection assembly 5 further includes a support column 52 and a through hole 53. The two ends of the four support columns 52 are respectively fixedly connected to the four arms 2 and the four elastic blocks 54. The support column 52 is located at one end of the elastic block 54 away from the through hole 53. The four through holes 53 are respectively opened on the four connection shells 51.

[0027] Further, as Figure 3 shown, a power supply 7 is arranged inside the fuselage 1. The four motors 3 are electrically connected to the power supply 7. The four electromagnets 56 are electrically connected to the power supply 7. When the power supply 7 is started, the electromagnet 56 is energized to attract the iron block 57 to move in the direction of the electromagnet 56.

[0028] Further, as Figure 1 and Figure 4 shown, the second connection assembly 6 includes a groove 61 and a rotating cover 62. The four grooves 61 are respectively opened on the four arms 2. The cross section of the groove 61 is arc-shaped. The rotating cover 62 is rotatably connected to the fuselage 1.

[0029] Further, as Figure 4 shown, the second connection assembly 6 further includes a fixing block 63 and a slider 64. The four fixing blocks 63 are fixedly connected to the rotating cover 62. The fixing blocks 63 are distributed in a circular array with the center of the rotating cover 62 as the center. The four sliders 64 are respectively slidably connected to the fuselage 1 and the four grooves 61. The four fixing blocks 63 are respectively slidably connected to the four sliders 64.

[0030] Further, as Figure 1 and Figure 4As shown, the second connecting component 6 also includes a limiting hole 65 and a latch 66. The limiting hole 65 is opened on the body 1, and the latch 66 is slidably connected to the rotating cover 62. The latch 66 is movably plugged into the limiting hole 65. When the limiting hole 65 and the latch 66 overlap, the slider 64 is embedded in the groove 61.

[0031] The specific working method is as follows: insert the machine arm 2 into the connecting shell 51, and one end of the elastic block 54 is embedded in the through hole 53. When it is necessary to disassemble, press the button 55 in the direction of the support column 52 to separate one end of the elastic block 54 from the through hole 53, and take out the machine arm 2. After the four machine arms 2 are installed, rotate the rotating cover 62, and the fixed block 63 rotates accordingly. Since the fixed block 63 is slidably connected to the slider 64, and the slider 64 is slidably connected to the machine body 1 and the groove 61, the slider 64 moves down with the rotation of the fixed block 63. When the slider 64 is When block 64 is embedded in groove 61, limiting hole 65 is just below latch 66. Latch 66 is moved downward to be embedded in limiting hole 65, thereby completing the fixation of rotating cover 62 and reinforcing arm 2. Power supply 7 is turned on. Since power supply 7 is electrically connected to electromagnet 56, electromagnet 56 is energized to attract iron block 57 and move it toward the bottom of elastic block 54. At this time, button 55 is pressed, and the bottom of elastic block 54 is held by iron block 57 and cannot move downward, thereby ensuring that arm 2 is completely fixed and cannot fall off during flight.

[0032] The technical means disclosed in the utility model are not limited to the technical means disclosed in the above technical means, but also include technical solutions composed of equivalent replacement of the above technical features. Matters not covered in the utility model belong to the common knowledge of those skilled in the art.

Claims

1. A quick disassembly and assembly structure of a vertical take-off and landing unmanned aerial vehicle arm, comprising a fuselage (1), four arms (2) movably plugged into the fuselage (1), four motors (3) respectively fixedly connected to the four arms (2), four wings (4) respectively arranged on the four motors (3), characterized in that: A first connecting assembly (5) is provided on the fuselage (1), the first connecting assembly (5) comprising a connecting shell (51), an elastic block (54), a button (55), an electromagnet (56), an iron block (57) and a spring (58); four connecting shells (51) are fixedly connected to the fuselage (1); four machine arms (2) are respectively slidably connected to the four connecting shells (51); four elastic blocks (54) are respectively fixedly connected to the four machine arms (2); four buttons (55) are respectively fixedly connected to the four elastic blocks (54); four electromagnets (56) are respectively fixedly connected to the four connecting shells (51); four iron blocks (57) are respectively slidably connected to the four connecting shells (51); two ends of a plurality of springs (58) are respectively fixedly connected to the four iron blocks (57) and the four connecting shells (51); and a second connecting assembly (6) is provided on the fuselage (1).

2. The quick disassembly and assembly structure of a vertical take-off and landing UAV arm according to claim 1, characterized in that: The first connection assembly (5) further comprises a support column (52) and a through hole (53), wherein two ends of the four support columns (52) are respectively fixedly connected to the four machine arms (2) and the four elastic blocks (54), and the four through holes (53) are respectively opened on the four connection shells (51).

3. The quick disassembly and assembly structure of a vertical take-off and landing UAV arm according to claim 1 is characterized in that: A power source (7) is provided in the body (1), the four motors (3) are electrically connected to the power source (7), and the four electromagnets (56) are electrically connected to the power source (7).

4. The quick disassembly and assembly structure of a vertical take-off and landing UAV arm according to claim 1, characterized in that: The second connection component (6) comprises a groove (61) and a rotating cover (62), wherein four grooves (61) are respectively provided on four machine arms (2), and the rotating cover (62) is rotatably connected to the machine body (1).

5. The quick disassembly and assembly structure of a vertical take-off and landing UAV arm according to claim 4 is characterized in that: The second connecting assembly (6) further comprises a fixed block (63) and a sliding block (64), wherein the four fixed blocks (63) are fixedly connected to the rotating cover (62), the four sliding blocks (64) are respectively slidably connected to the body (1) and the four grooves (61), and the four fixed blocks (63) are respectively slidably connected to the four sliding blocks (64).

6. The quick disassembly and assembly structure of a vertical take-off and landing UAV arm according to claim 4 is characterized in that: The second connecting component (6) further comprises a limiting hole (65) and a latch (66); the limiting hole (65) is formed on the body (1); and the latch (66) is slidably connected to the rotating cover (62).

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