Part assembling equipment for unmanned aerial vehicle production and using method thereof

Abstract

The invention relates to the field of industrial production equipment, and particularly discloses part assembling equipment for unmanned aerial vehicle production and a using method thereof. The dynamic screw screwing assembly assembly and the clamping and positioning assembly are arranged on the mounting frame, when multiple rotor wings of the unmanned aerial vehicle are assembled, the conveying belt can be controlled to drive the unmanned aerial vehicle body to the position below the dynamic screw screwing assembly assembly, the unmanned aerial vehicle body is stably clamped through the clamping and positioning assembly, and therefore the unmanned aerial vehicle body can be assembled. And then the dynamic screw screwing and assembling assembly is driven by the electric lifting rod to move downwards, meanwhile, the multiple rotor wing mounting screws on the unmanned aerial vehicle body are screwed, then the multiple rotor wings are rapidly and stably mounted on the unmanned aerial vehicle body, and compared with a traditional manual unmanned aerial vehicle assembling mode, the unmanned aerial vehicle rotor wing assembling device can effectively shorten the unmanned aerial vehicle rotor wing assembling time and improve the unmanned aerial vehicle rotor wing assembling efficiency. And the production efficiency of the unmanned aerial vehicle production line is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of industrial production equipment, and particularly relates to a component assembly device for UAV production and its usage method. Background Art

[0002] A multi-rotor UAV is an unmanned aerial vehicle that provides lift and controls flight through multiple rotors (usually four-rotor, six-rotor or eight-rotor). Its core principle is to adjust the rotation speed of each rotor to achieve actions such as ascending, descending, moving forward, moving backward, turning and hovering of the aircraft. The multi-rotor UAV has a simple structure and flexible control, and is widely used in fields such as aerial photography, agricultural plant protection, logistics distribution, environmental monitoring, and emergency rescue.

[0003] When assembling a multi-rotor UAV, it is necessary for the assembler to manually splice multiple components together. For example, when installing the propellers on the UAV cantilever, the operator needs to install multiple propellers one by one, and the entire assembly process takes a long time, resulting in too low assembly efficiency of the UAV. Summary of the Invention

[0004] In order to overcome the deficiencies of the prior art, the purpose of the present invention is to provide a component assembly device for UAV production and its usage method to solve the problem that the manual assembly process of traditional UAV rotors will reduce the production efficiency of the UAV production line.

[0005] To achieve the above purpose, the present invention provides the following technical solutions:

[0006] A component assembly device for UAV production, comprising:

[0007] An installation frame, including side plates, a bottom plate connected below the side plates, and a top plate connected above the side plates, and an electric lifting rod is fixedly connected to the top plate;

[0008] A dynamic screw screwing and assembling component, arranged on the telescopic end of the electric lifting rod;

[0009] A conveyor belt, arranged between the bottom plate and the top plate and located below the dynamic screw screwing and assembling component;

[0010] A driving motor, connected to the bottom plate, a lead screw is fixedly connected to the output shaft of the driving motor, a moving plate clamped on the side plate is threadedly connected to the lead screw, and a clamping and positioning component is connected to the moving plate.

[0011] Preferably, the dynamic screw screwing and assembling component includes a mounting frame fixedly installed on the electric lifting rod. Two sets of opposite chutes are respectively formed on the side surface of the mounting frame. Two sliding plates are slidably connected inside each set of chutes. The sliding plates inside the two sets of chutes are arranged staggeredly. An installation block is slidably connected at the staggered point of the two sets of staggered sliding plates. An electric screwdriver is fixedly connected to the installation block.

[0012] Preferably, an electric telescopic rod is fixedly connected inside the mounting frame. An installation plate is fixedly connected to the end of the electric telescopic rod. A hinge plate is hinged between the installation plate and the sliding plate.

[0013] Preferably, the electric telescopic rod is arranged in the middle of the inner wall of the mounting frame. And one installation plate and each two sliding plates in each group are provided with one hinge plate, and the two hinge plates are symmetrically arranged.

[0014] Preferably, the clamping and positioning component includes an intermediate plate fixedly installed on the moving plate and a first air pipe connected to the intermediate plate. A guide air pipe communicated with the first air pipe is connected inside the intermediate plate. An outer cylinder communicated with the guide air pipe is fixedly connected to the intermediate plate. An inner tube is slidably connected to the end of the outer cylinder. A spring is arranged inside the outer cylinder.

[0015] Preferably, one end of the spring abuts against the inner wall of the outer cylinder and the other end abuts against the end of the inner tube.

[0016] Preferably, a clamping plate is fixedly connected to the end of the inner tube away from the outer cylinder. And air holes communicated with the inner tube are formed in the clamping plate.

[0017] Preferably, lifting plates are respectively slidably connected to the upper and lower sides of the intermediate plate. A second air pipe is connected to the lifting plate. And an air passage communicated with the second air pipe is formed inside the lifting plate. An outer cylinder communicated with the air passage is also fixedly connected to the lifting plate. An inner tube is slidably connected to the end of the outer cylinder. A spring is arranged inside the outer cylinder.

[0018] Preferably, a partition plate is fixedly connected to the inner wall of the intermediate plate. The partition plate divides the internal space of the intermediate plate into upper and lower two chambers. The lifting plate is slidably connected inside the chamber. And a third air pipe is connected to the side wall of the intermediate plate and the third air pipe is communicated with the chamber.

[0019] A using method of a part assembling device for unmanned aerial vehicle production, which is applied to a part assembling device for unmanned aerial vehicle production, includes:

[0020] Transport the unmanned aerial vehicle body and the rotor with unfastened screws to the lower part of the dynamic screw screwing and assembling component through the conveyor belt;

[0021] The driving motor drives the lead screw to rotate, and the rotating lead screw drives the moving plate to displace, so that the clamping and positioning assembly adheres to the side of the UAV body and clamps the UAV body;

[0022] The electric lifting rod extends to move the dynamic screw screwing and assembling assembly above the UAV body, and the dynamic screw screwing and assembling assembly simultaneously screws multiple rotor mounting screws on the UAV body;

[0023] The clamping and positioning assembly releases the UAV body, and the conveyor belt transports the UAV body to the next working step.

[0024] Compared with the prior art, the beneficial effects of the present invention are:

[0025] By arranging the dynamic screw screwing and assembling assembly and the clamping and positioning assembly on the mounting frame, when assembling multiple rotors of the UAV, the conveyor belt can be controlled to drive the UAV body below the dynamic screw screwing and assembling assembly. The clamping and positioning assembly stably clamps the UAV body, and then the electric lifting rod drives the dynamic screw screwing and assembling assembly to move down, simultaneously screwing multiple rotor mounting screws on the UAV body, so as to quickly and stably install multiple rotors on the UAV body. Compared with the traditional manual UAV assembly method, using this device can effectively reduce the UAV rotor assembly time, thereby improving the production efficiency of the UAV production line. Description of the Drawings

[0026] Figure 1 is the overall structural schematic diagram of the present invention;

[0027] Figure 2 is the structural schematic diagram of the dynamic screw screwing and assembling assembly of the present invention Figure 1 ;

[0028] Figure 3 is the structural schematic diagram of the dynamic screw screwing and assembling assembly of the present invention Figure 2 ;

[0029] Figure 4 is the structural schematic diagram of the clamping and positioning assembly of the present invention Figure 1 ;

[0030] Figure 5 is the structural schematic diagram of the clamping and positioning assembly of the present invention Figure 2 ;

[0031] Figure 6 is the cross-sectional structural schematic diagram of the clamping and positioning assembly of the present invention;

[0032] In the figure: 1, side plate; 2, bottom plate; 3, top plate; 4, electric lifting rod; 5, mounting frame; 51, chute; 52, sliding plate; 53, mounting block; 54, electric telescopic rod; 55, mounting plate; 56, hinged plate; 6, electric screwdriver; 7, conveyor belt; 8, drive motor; 9, lead screw; 10, moving plate; 11, clamping and positioning assembly; 111, intermediate plate; 112, first air pipe; 113, air guide pipe; 114, outer cylinder; 115, inner pipe; 116, spring; 117, clamping plate; 118, air hole; 119, lifting plate; 120, second air pipe; 121, partition plate; 122, third air pipe. Specific embodiments

[0033] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0034] Embodiment 1:

[0035] Please refer to Figure 1 - Figure 6 As shown in the figure, a part assembly device for UAV production includes:

[0036] A mounting frame, including a side plate 1, a bottom plate 2 connected below the side plate 1, and a top plate 3 connected above the side plate 1. An electric lifting rod 4 is fixedly connected to the top plate 3;

[0037] A dynamic screw screwing and assembling component is arranged on the telescopic end of the electric lifting rod 4;

[0038] A conveyor belt 7 is arranged between the bottom plate 2 and the top plate 3 and is located below the dynamic screw screwing and assembling component;

[0039] A drive motor 8 is connected to the bottom plate 2. The output shaft of the drive motor 8 is fixedly connected with a lead screw 9. A moving plate 10 clamped on the side plate 1 is threadedly connected to the lead screw 9, and a clamping and positioning assembly 11 is connected to the moving plate 10.

[0040] As can be seen from the above, by providing a dynamic screw-tightening assembly component and a clamping and positioning component 11 on the mounting bracket, when assembling multiple rotors of a drone, the conveyor belt can be controlled to drive the drone body under the dynamic screw-tightening assembly component. The clamping and positioning component 11 stably clamps the drone body, and then the electric lifting rod 4 drives the dynamic screw-tightening assembly component to move downward, while screwing multiple rotor mounting screws on the drone body, thereby quickly and stably installing multiple rotors on the drone body. Compared with the traditional manual drone assembly method, using this device can effectively reduce the assembly time of drone rotors, thereby improving the production efficiency of the drone production line.

[0041] Please refer to Figure 1 - Figure 3 As shown in the figure, the dynamic screw-tightening assembly component includes a mounting frame 5 fixedly installed on the electric lifting rod 4. Two sets of oppositely arranged sliding grooves 51 are respectively formed on the side surface of the mounting frame 5. Two sliding plates 52 are slidably connected inside each set of sliding grooves 51. The sliding plates 52 inside the two sets of sliding grooves 51 are arranged staggeredly. An installation block 53 is slidably connected at the staggered point of the two sets of staggered sliding plates 52. An electric screwdriver 6 is fixedly connected to the installation block 53. An electric telescopic rod 54 is fixedly connected inside the mounting frame 5. An installation plate 55 is fixedly connected to the end of the electric telescopic rod 54. A hinge plate 56 is hinged between the installation plate 55 and the sliding plate 52.

[0042] As can be seen from the above, when screwing the rotor screws on drones of different specifications, the operator can drive the installation plate 55 to move through the telescopic movement of the electric telescopic rod 54. The moving installation plate 55 will drive the hinge plate 56 to rotate. The rotating hinge plate 56 will support the sliding plates 52 on both sides of the electric telescopic rod 54 with the installation plate 55 as the fulcrum, causing the sliding plates 52 to slide inside the sliding grooves 51. The sliding plates 52 move the installation block 53 to a suitable position, thereby adjusting the electric screwdriver 6 below the installation block 53 to a suitable position, so that the electric screwdriver 6 is aligned with the rotor mounting screw on the drone body. The electric lifting rod 4 drives the mounting frame 5 to move downward, so that the end of the electric screwdriver 6 is inserted into the rotor mounting screw, and controlling the rotation of the electric screwdriver 6 can complete the installation of the rotor.

[0043] The electric telescopic rod 54 is arranged in the middle of the inner wall of the mounting frame 5, and a hinge plate 56 is arranged between one mounting plate 55 and every two sliding plates 52 in each group. The two hinge plates 56 are symmetrically arranged. When one electric telescopic rod 54 expands and contracts, it can drive the two hinge plates 56 to rotate, and drive the two sliding plates 52 in each group to slide synchronously through the two hinge plates 56, so that the two electric screwdrivers 6 can be displaced synchronously to align with the rotor mounting screws. Generally, the rotors of multi-rotor UAVs are symmetrically arranged. Synchronously adjusting the settings of multiple electric screwdrivers 6 can better cope with the rotor assembly scenarios of multi-rotor UAVs.

[0044] Please refer to Figure 1 , Figure 4 - Figure 6 As shown in the figure, the clamping and positioning assembly 11 includes an intermediate plate 111 fixedly installed on the moving plate 10 and a first air pipe 112 connected to the intermediate plate 111. A guide air pipe 113 communicating with the first air pipe 112 is connected inside the intermediate plate 111. An outer cylinder 114 communicating with the guide air pipe 113 is fixedly connected to the intermediate plate 111. An inner tube 115 is slidably connected to the end of the outer cylinder 114. A spring 116 is arranged inside the outer cylinder 114. One end of the spring 116 abuts against the inner wall of the outer cylinder 114, and the other end abuts against the end of the inner tube 115.

[0045] When the output shaft of the driving motor 8 drives the lead screw 9 to rotate, the lead screw 9 will drive the moving plate 10 to displace. The displaced moving plate 10 will drive the intermediate plate 111 to displace. The displaced intermediate plate 111 makes the ends of multiple inner tubes 115 fit on the surface of the UAV body. Some inner tubes 115 will retract into the outer cylinder 114 to compress the spring 116. The lengths of different inner tubes 115 retracting into the outer cylinder 114 are different, which is convenient for the ends of the inner tubes 115 at different positions to fit on the UAV body. When the inner tube 115 fits tightly, a negative pressure environment is formed inside the outer cylinder 114 through the first air pipe 112 and the guide air pipe 113, so that the surface of the UAV body is adsorbed together with the end of the inner tube 115, which can effectively increase the clamping stability of the UAV body.

[0046] Because the area of the end of the inner tube 115 is too small, in order to avoid excessive contact pressure between the end of the inner tube 115 and the surface of the drone body, the end of the inner tube 115 away from the outer tube 114 is fixedly connected with a splint 117. The splint 117 can be made of a deformable rubber material, and the splint 117 is provided with an air hole 118 connected to the inner tube 115. When negative pressure is formed inside the inner tube 115, the inside of the air hole 118 is connected to the inner tube 115 to form a negative pressure environment. At this time, the external pressure will force the splint 117 to deform and adhere to the surface of the drone body. The splint 117 can increase the clamping area of the drone body surface and avoid excessive pressure on the drone as much as possible without affecting the clamping force.

[0047] The upper and lower sides of the middle plate 111 are respectively slidably connected with a lifting plate 119, the lifting plate 119 is connected with a second air pipe 120, and an air passage connected to the second air pipe 120 is opened inside the lifting plate 119, and an outer tube 114 connected to the air passage is also fixedly connected to the lifting plate 119, an inner tube 115 is slidably connected to the end of the outer tube 114, and a spring 116 is arranged inside the outer tube 114.

[0048] The inner wall of the middle plate 111 is fixedly connected with a partition 121, and the partition 121 divides the internal space of the middle plate 111 into two upper and lower chambers. The lifting plate 119 is slidably connected inside the chamber, and the side wall of the middle plate 111 is connected with a third air pipe 122, and the third air pipe 122 is connected to the chamber.

[0049] As can be seen from the above, the user can fill the interior of the chamber with gas through the third air pipe 122, and use the air pressure to drive the lifting plate 119 to extend out of the middle plate 111. Then, a negative pressure environment is also formed in the outer tube 114 and the inner tube 115 through the second air pipe 120 and the air duct. By increasing the number of inner tubes 115 and splints 117, the clamping stability of the drone body is improved, and shaking of the drone body during assembly is avoided.

[0050] A method for using a parts assembly device for producing a drone, applied to a parts assembly device for producing a drone, comprising:

[0051] The drone body and rotor with untightened screws are transported to the bottom of the dynamic screw tightening assembly component by the conveyor belt 7;

[0052] The driving motor 8 drives the lead screw 9 to rotate. The rotating lead screw 9 drives the moving plate 10 to displace, and the moving plate 10 drives the intermediate plate 11 to move. At the same time, the user can adjust the height of the lifting plate 119 extending out of the intermediate plate 11 through the third air pipe 122, and thus can adjust the distance between the upper and lower clamping plates 117. Then, a negative pressure environment is formed inside the guide air pipe 113 and the air passage through the first air pipe 112 and the second air pipe 120, so that a negative pressure environment is formed inside all the outer cylinders 114 and the inner pipes 115, causing the clamping plates 117 to closely adhere to the surface of the UAV body under the action of atmospheric pressure and stably clamp the UAV body;

[0053] The electric lifting rod 4 extends, causing the mounting frame 5 to move above the UAV body. The electric telescopic rod 54 is started to drive the mounting block 55 to move. The moving mounting block 55 drives the hinged plate 56 to rotate, and the rotating hinged plate 56 drives the sliding plate 52 to slide inside the chute 51. The sliding sliding plate 52 drives the mounting block 53 to move, and the moving mounting block 53 drives the electric screwdriver 6 to move, so that the electric screwdriver 6 is aligned with the rotor mounting screws on the UAV cantilever, and at the same time, multiple rotor mounting screws on the UAV body are screwed;

[0054] After the rotors are installed, the driving motor 8 drives the lead screw 9 to turn over, so that the clamping and positioning assembly 11 releases the UAV body, and the conveyor belt 7 transports the UAV body to the next process.

[0055] The standard parts used in the present invention can all be purchased from the market. The special-shaped parts can be customized according to the description of the specification and the drawings. The specific connection methods of each part all adopt conventional means such as bolts, rivets, and welding that are mature in the prior art. The machines, parts, and equipment all adopt conventional models in the prior art. In addition, the circuit connection adopts the conventional connection method in the prior art, which will not be elaborated here. The content not described in detail in this specification belongs to the prior art well-known to those skilled in the art.

[0056] In the description of the present invention, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. The meaning of "a plurality" is two or more, unless otherwise specifically defined.

[0057] In the present invention, unless otherwise clearly defined or limited, terms such as "installed", "connected", "joined", "fixed", etc. shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the internal communication of two components or the interaction relationship between two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0058] In the present invention, unless otherwise clearly defined or limited, the first feature being "on" or "under" the second feature may be that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may be that the first feature is directly above or obliquely above the second feature, or merely indicates that the first feature has a higher horizontal height than the second feature. The first feature being "under", "below" and "beneath" the second feature may be that the first feature is directly below or obliquely below the second feature, or merely indicates that the first feature has a lower horizontal height than the second feature.

[0059] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "example", "specific example" or "some examples", etc. means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic descriptions of the above terms do not have to be directed to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0060] In the drawings of the disclosed embodiments of the present invention, only the structures related to the disclosed embodiments are involved, and other structures can refer to the general design. Without conflict, the same embodiment and different embodiments of the present invention can be combined with each other.

Claims

1. A parts assembly device for drone production, characterized in that, Comprising: An installation frame, including side plates (1), a bottom plate (2) connected below the side plates (1), and a top plate (3) connected above the side plates (1), an electric lifting rod (4) is fixedly connected to the top plate (3); A dynamic screw screwing and assembling component, arranged on the telescopic end of the electric lifting rod (4); A conveyor belt (7), arranged between the bottom plate (2) and the top plate (3) and located below the dynamic screw screwing and assembling component; A driving motor (8), connected to the bottom plate (2), a lead screw (9) is fixedly connected to the output shaft of the driving motor (8), a moving plate (10) clamped on the side plate (1) is threadedly connected to the lead screw (9), and a clamping and positioning component (11) is connected to the moving plate (10).

2. The component assembly device for UAV production according to claim 1, characterized in that: The dynamic screw screwing and assembling component includes a mounting frame (5) fixedly installed on the electric lifting rod (4), two groups of oppositely arranged sliding grooves (51) are respectively formed on the side surface of the mounting frame (5), two sliding plates (52) are slidably connected inside each group of sliding grooves (51), the sliding plates (52) inside the two groups of sliding grooves (51) are staggered, an installation block (53) is slidably connected at the staggered point of the two groups of staggered sliding plates (52), and an electric screwdriver (6) is fixedly connected to the installation block (53).

3. The parts assembling device for UAV production according to claim 2, wherein: An electric telescopic rod (54) is fixedly connected inside the mounting frame (5), a mounting plate (55) is fixedly connected to the end of the electric telescopic rod (54), and a hinge plate (56) is hinged between the mounting plate (55) and the sliding plate (52).

4. The component assembly device for UAV production according to claim 3, characterized in that: The electric telescopic rod (54) is arranged in the middle of the inner wall of the mounting frame (5), and one mounting plate (55) and each two sliding plates (52) are provided with one hinge plate (56), and the two hinge plates (56) are symmetrically arranged.

5. The component assembly device for UAV production according to claim 1, characterized in that: The clamping and positioning component (11) includes an intermediate plate (111) fixedly installed on the moving plate (10) and a first air pipe (112) connected to the intermediate plate (111), a guide air pipe (113) communicated with the first air pipe (112) is connected inside the intermediate plate (111), an outer cylinder (114) communicated with the guide air pipe (113) is fixedly connected to the intermediate plate (111), an inner tube (115) is slidably connected to the end of the outer cylinder (114), and a spring (116) is arranged inside the outer cylinder (114).

6. The parts assembly device for UAV production according to claim 5, wherein: One end of the spring (116) abuts against the inner wall of the outer cylinder (114), and the other end abuts against the end of the inner tube (115).

7. An assembly device for parts used in the production of drones according to claim 5, characterized in that: One end of the inner tube (115) far from the outer cylinder (114) is fixedly connected with a clamping plate (117), and air holes (118) communicated with the inner tube (115) are formed in the clamping plate (117).

8. The component assembly device for UAV production according to claim 5, characterized in that: The upper and lower sides of the middle plate (111) are respectively connected with lifting plates (119) in a sliding manner. A second air pipe (120) is connected to the lifting plate (119), and an air passage communicating with the second air pipe (120) is provided inside the lifting plate (119). An outer cylinder (114) communicating with the air passage is also fixedly connected to the lifting plate (119). An inner tube (115) is connected to the end of the outer cylinder (114) in a sliding manner, and a spring (116) is arranged inside the outer cylinder (114).

9. The parts assembly device for UAV production according to claim 8, characterized in that: A partition plate (121) is fixedly connected to the inner wall of the middle plate (111). The partition plate (121) divides the internal space of the middle plate (111) into upper and lower chambers. The lifting plate (119) is slidably connected inside the chamber. A third air pipe (122) is connected to the side wall of the middle plate (111), and the third air pipe (122) communicates with the chamber.

10. A method for using a component assembly device for UAV production, characterized in that, Applied to a component assembly device for unmanned aerial vehicle production according to any one of claims 1-9, comprising: The conveyor belt (7) is used to transport the unmanned aerial vehicle body and the rotor without tightened screws to the lower part of the dynamic screw screwing and assembling assembly; The driving motor (8) drives the lead screw (9) to rotate. The moving plate (10) is displaced by the rotating lead screw (9), so that the clamping and positioning assembly (11) adheres to the side of the unmanned aerial vehicle body and clamps the unmanned aerial vehicle body; The electric lifting rod (4) extends to move the dynamic screw screwing and assembling assembly above the unmanned aerial vehicle body, and a plurality of rotor mounting screws on the unmanned aerial vehicle body are simultaneously screwed by the dynamic screw screwing and assembling assembly; The clamping and positioning assembly (11) releases the unmanned aerial vehicle body, and the conveyor belt (7) transports the unmanned aerial vehicle body to the next process.

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