Arm folding mechanism of lightweight unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a lightweight unmanned aerial vehicle arm folding mechanism which comprises a plurality of vehicle arms arranged on a vehicle body and used for supporting propellers. The joints are provided with moving spaces, and one ends of the arms are rotationally arranged in the moving spaces and can vertically move along the moving spaces; the elastic assembly is arranged in the moving space and used for pushing one end of the machine arm to be attached to the connector. The clamping parts are arranged on the arms and the connectors respectively, so that a clamping structure for locking rotation of the arms can be formed, and compared with a traditional mode that the arms and the connectors are abraded to finally cause loosening due to friction force fixation, loosening caused by abrasion can be avoided through locking by means of the clamping structure, the structure is more stable, and the reliability is improved. Arm rotation caused by mistaken touch can be prevented, the problem of loosening caused by abrasion does not need to be worried about, and the service life of the unmanned aerial vehicle is longer.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a lightweight UAV arm folding mechanism. Background Technology

[0002] Currently, most drones on the market use a simple shaft to fix the arms to the fuselage, relying on friction for rotational fixation. When not in use, the arms can be rotated relative to the fuselage to fold them into the side, reducing the drone's size and making storage easier. However, the drawback of this friction-resistance fixing structure is that the fastening effect decreases with the number of uses (rotations). Wear can cause the arms to loosen at the rotation points, making them prone to rotation and affecting usability. In addition, the continuous vibrations during drone flight, as well as collisions and falls, further exacerbate this problem. Therefore, a new folding mechanism is needed. Utility Model Content

[0003] In view of this, the purpose of this utility model is to propose a lightweight drone arm folding mechanism to solve the technical problem that the connection between the arm and the fuselage of existing drones will loosen after long-term use.

[0004] To achieve the above objectives, this utility model provides a lightweight unmanned aerial vehicle (UAV) arm folding mechanism, comprising:

[0005] Several arms mounted on the fuselage to support the propeller;

[0006] Multiple joints with movable space are provided, and one end of the arm is rotatably located in the movable space and can move vertically along the movable space;

[0007] An elastic component is provided in the activity space to push one end of the robot arm to keep it in contact with the connector, so that the robot arm and the connector form a contacting surface;

[0008] A first engaging portion is provided on the contact surface of the arm;

[0009] The second engaging part, located on the mating surface of the connector and cooperating with the first engaging part, can be engaged and disengaged by rotating the machine arm, thereby locking and unlocking the rotation of the machine arm.

[0010] As a preferred embodiment of this utility model, the first engaging part is a protrusion on the upper surface of one end of the machine arm, and the second engaging part is a groove on the upper surface of the joint's movable space. When the protrusion engages with the groove, it can prevent the machine arm from rotating relative to the joint.

[0011] As a preferred embodiment of this utility model, a shaft is provided in the movable space of the joint, and the shaft is rotatably engaged with a first through hole opened at one end of the arm.

[0012] As a preferred embodiment of this utility model, the elastic component includes a spring located at the lower end of the arm and the upper end of the joint.

[0013] As a preferred embodiment of this utility model, a first washer and a second washer are sleeved on the surface of the shaft, and the two ends of the spring abut against the upper end face of the first washer and the lower end face of the second washer, respectively.

[0014] As a preferred embodiment of this utility model, the shaft is a positioning bolt that passes through a second through hole on the surface of the joint. The lower end of the positioning bolt passes through the second through hole and is connected to a positioning nut. The positioning nut engages with a limiting ring located at the lower end of the joint.

[0015] As a preferred embodiment of this utility model, the second engaging portion is provided with at least two angles corresponding to the folded and unfolded states of the arm, respectively.

[0016] As a preferred embodiment of this invention, the folding mechanism further includes:

[0017] A first connecting rod with one end fixedly connected to the arm;

[0018] A first snap-fit ​​component connected to the other end of the first connecting rod;

[0019] A second connecting rod, one end of which is fixedly connected to the fuselage;

[0020] A second latching member is connected to the other end of the second connecting rod. The second latching member is located on the movement trajectory of the first latching member. By rotating the machine arm, the first latching member and the second latching member can be latched and separated, so as to fix the first connecting rod and the second connecting rod through the first latching member and the second latching member.

[0021] As a preferred embodiment of this utility model, the first snap-fit ​​component is a round bar connected to the first connecting rod, and the second snap-fit ​​component is a slot formed at one end of the second connecting rod. The end of the slot is formed with a flange structure for preventing the round bar from leaving the slot, and the flange structure is deformable.

[0022] The beneficial effects of this utility model are as follows: By setting locking parts on the arm and the connector respectively, this utility model can form a locking structure that locks the arm rotation. Compared with the traditional friction fixing, which will wear down the arm and connector and eventually cause loosening, the locking structure can avoid loosening due to wear. Not only is the structure more stable and can prevent the arm from rotating due to accidental contact, but there is also no need to worry about loosening caused by wear, and the service life of the drone is longer. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only for this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 This is a three-dimensional structural diagram of the folded arm of this utility model;

[0025] Figure 2 This is a three-dimensional structural diagram of the arm of this utility model in the deployed state;

[0026] Figure 3 For the present utility model Figure 2 Enlarged structural diagram at point A in the middle;

[0027] Figure 4 This is a schematic diagram of the bottom three-dimensional structure of this utility model;

[0028] Figure 5 This is a three-dimensional structural diagram of the arm and connector of this utility model;

[0029] Figure 6 This is a three-dimensional structural diagram of the arm and connector of this utility model.

[0030] The markings in the diagram are as follows: 1. Body; 2. Connector; 3. Arm; 4. Positioning bolt; 5. Second through hole; 6. First through hole; 7. Positioning nut; 8. Limiting ring; 9. First washer; 10. Second washer; 11. Spring; 12. First engaging part; 13. Second engaging part; 14. First connecting rod; 15. First locking piece; 16. Second connecting rod; 17. Second locking piece. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to specific embodiments.

[0032] It should be noted that, unless otherwise defined, the technical or scientific terms used in this utility model should have the ordinary meaning understood by one of ordinary skill in the art to which this utility model pertains. The terms "first," "second," and similar terms used in this utility model do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Terms such as "comprising" or "including" mean that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, without excluding other elements or objects. Terms such as "connected" or "linked" are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. Terms such as "upper," "lower," "left," and "right" are used only to indicate relative positional relationships; when the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0033] like Figure 1 , Figure 2 and Figure 3 As shown, a lightweight unmanned aerial vehicle (UAV) arm folding mechanism includes: a plurality of arms 3 mounted on the fuselage 1 for supporting propellers; a plurality of joints 2 with movable spaces, one end of each arm 3 being rotatably mounted in the movable space and capable of vertical movement along the movable space; an elastic component mounted in the movable space for pushing one end of the arm 3 to maintain contact with the joint 2, so that the arm 3 and the joint 2 form a contacting surface; a first engaging portion 12 mounted on the contacting surface of the arm 3; and a second engaging portion 13 mounted on the contacting surface of the joint 2 and cooperating with the first engaging portion 12, wherein rotating the arm 3 can cause the first engaging portion 12 and the second engaging portion 13 to engage and disengage, thereby locking and unlocking the rotation of the arm 3.

[0034] The above technical solution effectively improves the connection stability between the arm 3 and the fuselage 1, preventing loosening. During use, the arm 3 is rotated within the movable space of the connector 2, allowing it to rotate relative to the fuselage 1 and unfold for normal use. When the arm 3 rotates to a preset position, the first engaging part 12 on the arm 3 engages with the second engaging part 13 of the connector 2, thus restricting the rotation of the arm 3 and preventing rotation due to vibration or external force. When the drone is not in use and the arm 3 needs to be stored, pressing the arm 3 compresses the elastic component, ensuring the first engaging part 12 on the arm 3 remains engaged. 2 will disengage from the second engaging part 13 of the connector 2, releasing the rotation restriction of the arm 3. Then the arm 3 can be rotated to return to its initial position. Release the arm 3, and the elastic component will drive the arm 3 to rise and reset, so that the first engaging part 12 on the arm 3 will engage with the second engaging part 13 of the connector 2 again, locking the rotation of the arm 3. Compared with the traditional friction fixing, which will wear down the arm 3 and the connector 2 and eventually cause loosening, this utility model relies on the engaging structure to lock, which can avoid wear and loosening. Not only is the structure more stable, it can prevent the arm 3 from rotating due to accidental contact, but there is also no need to worry about wear causing loosening, and the service life of the drone is longer.

[0035] like Figure 5 and Figure 6 As shown, in this embodiment, the first engaging part 12 is a protrusion on the upper surface of one end of the arm 3, and the second engaging part 13 is a groove on the upper surface of the movable space of the connector 2. When the protrusion is engaged in the groove, it can prevent the arm 3 from rotating relative to the connector 2. A shaft is provided in the movable space of the connector 2, and the shaft is rotatably engaged with the first through hole 6 opened at one end of the arm 3.

[0036] The above technical solution can lock the rotation of the machine arm 3 by the cooperation of the protrusion and the groove. When the protrusion is embedded in the groove, the machine arm 3 cannot rotate. When the protrusion is dislodged from the groove, the machine arm 3 can resume rotation.

[0037] like Figure 2 , Figure 3 and Figure 4 As shown, in this embodiment, the elastic component includes a spring 11 disposed at the lower end of the arm 3 and the upper end of the connector 2; preferably, a first washer 9 and a second washer 10 are sleeved on the surface of the shaft, and the two ends of the spring 11 abut against the upper end surface of the first washer 9 and the lower end surface of the second washer 10, respectively.

[0038] The above technical solution can ensure that the arm 3 can always be in contact with the connector 2. The spring 11 pushes the arm 3 to rise along the axis, so that the upper end face of the arm 3 is in contact with the lower end face of the top of the inner top of the movable space of the connector 2, thereby ensuring the stable connection between the first engaging part 12 and the second engaging part 13.

[0039] like Figure 4 , Figure 5 and Figure 6 As shown, in this embodiment, the shaft is a positioning bolt 4 that passes through the second through hole 5 on the surface of the connector 2. The lower end of the positioning bolt 4 passes through the second through hole 5 and is connected to a positioning nut 7. The positioning nut 7 engages with a limiting ring 8 located at the lower end of the connector 2. Preferably, the second engaging part 13 is provided with at least two parts to correspond to the angles of the folded and unfolded states of the arm 3, respectively.

[0040] The above technical solution allows for easy disassembly of the arm 3. When the arm 3 needs to be disassembled for maintenance, the positioning bolt 4 can be rotated relative to the positioning nut 7 to separate the two. Then, the positioning bolt 4 can be pulled out from the second through hole 5 on the surface of the connector 2, thereby removing the arm 3 from the movable space of the connector 2.

[0041] like Figure 1 and Figure 2 As shown, in this embodiment, the folding mechanism further includes: a first connecting rod 14 fixedly connected to the arm 3 at one end; a first latching member 15 connected to the other end of the first connecting rod 14; a second connecting rod 16 fixedly connected to the body 1 at one end; and a second latching member 17 connected to the other end of the second connecting rod 16. The second latching member 17 is located on the movement trajectory of the first latching member 15. By rotating the arm 3, the first latching member 15 and the second latching member 17 can be latched and separated, so as to fix the first connecting rod 14 and the second connecting rod 16 through the first latching member 15 and the second latching member 17. Preferably, the first latching member 15 is a round bar connected to the first connecting rod 14, and the second latching member 17 is a slot formed at one end of the second connecting rod 16. The end of the slot is formed with a flange structure for preventing the round bar from leaving the slot. The flange structure is deformable.

[0042] The above technical solution can further improve the connection stability of the robotic arm 3. When the robotic arm 3 is extended, it will drive the first connecting rod 14 on its surface to rotate. The first connecting rod 14 drives the first locking piece 15 to engage with the second locking piece 17 at one end of the second connecting rod 16 on the side of the body 1. This allows the robotic arm 3 to be supported and fixed to the body 1 through the first connecting rod 14 and the second connecting rod 16, thereby improving the support strength of the robotic arm 3. Since the second locking piece 17 engages or disengages with the first locking piece 15 by rotation, in order to avoid motion interference, the second locking piece 17, i.e., the slot, should be larger. At the same time, the second locking piece 17 and the second connecting rod 16 can be made of plastic deformable material.

[0043] Working principle: In use, rotating arm 3 within the movable space of connector 2 allows arm 3 to rotate relative to the fuselage 1, thus unfolding arm 3 for normal use. When arm 3 rotates to a preset position, the first engaging part 12 on arm 3 engages with the second engaging part 13 of connector 2, restricting the rotation of arm 3 and preventing rotation due to vibration or external force. Simultaneously, when arm 3 unfolds, it drives the first connecting rod 14 on its surface to rotate. The first connecting rod 14 drives the first engaging piece 15 to engage with the second engaging piece 17 at one end of the second connecting rod 16 on the side of fuselage 1. This ensures that arm 3 is supported and fixed to fuselage 1 via the first connecting rod 14 and the second connecting rod 16, increasing the support strength of arm 3. When the drone is not in use, it needs to be unfolded. When retracting the arm 3, pressing the arm 3 causes the spring 11 to be compressed, thereby ensuring that the first engaging part 12 on the arm 3 disengages from the second engaging part 13 of the connector 2, releasing the rotation restriction of the arm 3. Then, the arm 3 can be rotated to return to its initial position. Releasing the arm 3 causes the spring 11 to lift and reset the arm 3, so that the first engaging part 12 on the arm 3 engages with the second engaging part 13 of the connector 2 again, locking the rotation of the arm 3. Compared with the traditional friction fixing, which can wear down the arm 3 and the connector 2 and eventually cause loosening, this utility model relies on the engaging structure to lock, which can avoid wear and loosening. Not only is the structure more stable and can prevent the arm 3 from rotating due to accidental contact, but there is also no need to worry about wear causing loosening, resulting in a longer service life for the drone.

[0044] Those skilled in the art should understand that the discussion of any of the above embodiments is merely exemplary and is not intended to imply that the scope of the present invention (including the claims) is limited to these examples; within the framework of the present invention, the technical features of the above embodiments or different embodiments can also be combined, the steps can be implemented in any order, and there are many other variations of the different aspects of the present invention as described above, which are not provided in the details for the sake of brevity.

[0045] This utility model is intended to cover all such substitutions, modifications, and variations that fall within the broad scope of the appended claims. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A folding mechanism for the arms of a lightweight unmanned aerial vehicle, comprising: a plurality of arms (3) provided on a fuselage (1) for supporting propellers; characterized in that the folding mechanism further comprises: a plurality of joints (2) having a space for rotation, one end of each arm (3) being rotatably arranged in the space and vertically movable along the space; a resilient component provided in the space for pushing one end of each arm (3) to keep it in close contact with the joint (2) so that the arm (3) and the joint (2) form a close contact surface for mutual contact; a first clamping part (12) provided on the close contact surface of the arm (3); a second clamping part (13) provided on the close contact surface of the joint (2) and matched with the first clamping part (12), the first clamping part (12) and the second clamping part (13) being clamped and separated by rotating the arm (3) to lock and unlock the rotation of the arm (3). 2.The folding mechanism of a lightweight unmanned aerial vehicle according to claim 1, wherein, The first clamping part (12) is a protrusion provided on the upper surface of one end of the arm (3), and the second clamping part (13) is a groove provided on the upper surface of the space in the joint (2), the rotation of the arm (3) relative to the joint (2) being prevented when the protrusion is clamped into the groove. 3.The folding mechanism of the lightweight unmanned aerial vehicle according to claim 2, wherein An axle is arranged in the space of the joint (2), and the axle is rotatably matched with a first through hole (6) provided on one end of the arm (3). 4.The folding mechanism of a lightweight unmanned aerial vehicle according to claim 3, wherein, The resilient component comprises a spring (11) arranged at the lower end of the arm (3) and the upper end of the joint (2). 5.The folding mechanism of the lightweight unmanned aerial vehicle according to claim 4, wherein, The surface of the axle is sleeved with a first washer (9) and a second washer (10), and the two ends of the spring (11) are respectively in contact with the upper end surface of the first washer (9) and the lower end surface of the second washer (10). 6.The folding mechanism of the lightweight unmanned aerial vehicle according to claim 5, wherein The axle is a positioning bolt (4) penetrating a second through hole (5) provided on the surface of the joint (2), the lower end of the positioning bolt (4) penetrates the second through hole (5) and is connected with a positioning nut (7), and the positioning nut (7) is clamped and matched with a limiting ring (8) arranged at the lower end of the joint (2). 7.The folding mechanism of the lightweight unmanned aerial vehicle according to claim 2, wherein The second clamping part (13) is provided with at least two parts corresponding to the angles of the folded state and the unfolded state of the arm (3). 8.The arm folding mechanism of a light-weighted unmanned aerial vehicle according to claim 1, wherein The folding mechanism further comprises: a first connecting rod (14) fixedly connected with the arm (3); a first clamping member (15) connected with the other end of the first connecting rod (14); a second connecting rod (16) fixedly connected with the fuselage (1); a second clamping member (17) connected with the other end of the second connecting rod (16), the second clamping member (17) being located on the active track of the first clamping member (15), the first clamping member (15) and the second clamping member (17) being clamped and separated by rotating the arm (3) to fix the first connecting rod (14) and the second connecting rod (16) through the first clamping member (15) and the second clamping member (17). 9.The folding mechanism of the lightweight unmanned aerial vehicle according to claim 8, wherein, The first clamping member (15) is a round bar connected with the first connecting rod (14), and the second clamping member (17) is a clamping groove provided on one end of the second connecting rod (16), the end of the clamping groove being formed with a flange structure for preventing the round bar from leaving the clamping groove, and the flange structure being deformable.

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