A multi-rotor drone

Abstract

This invention discloses a multi-rotor drone, relating to the field of drone technology. The multi-rotor drone includes an upper fuselage and a lower frame. The frame includes a set of symmetrically mounted support legs below the fuselage. Each support leg includes a pair of parallel uprights. A lifting screw is rotatably mounted within each upright, and a lifting ring is threaded onto the lifting screw. A clamping assembly is mounted on the lifting ring. When additional equipment is mounted below the multi-rotor drone, since different additional equipment has different mounting heights below the drone, a mounting plate is pre-set on the top of the additional equipment. The mounting plate needs to be placed between the clamping assemblies. In other words, a controllable clamping assembly is provided on the frame below the drone, enabling quick assembly and disassembly of different additional equipment.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically to a multi-rotor UAV. Background Technology

[0002] In the field of drone technology, different types of drones are needed for different application scenarios, and the demand for underwater exploration is gradually increasing.

[0003] The existing patent with publication number CN221642666U specifically discloses a magnetic delivery device and a drone equipped with the device. The drone mentioned includes a central frame, a landing gear mounted below the frame, and additional equipment mounted on the frame and the landing gear.

[0004] However, in use, different auxiliary equipment usually needs to be mounted on the underside of the multi-rotor drone to enable it to complete different auxiliary tasks. There is an urgent need for an installation structure that can be conveniently used to fix different auxiliary equipment. Summary of the Invention

[0005] In view of the above-mentioned technical deficiencies, the technical problem to be solved by the present invention is to provide a multi-axis unmanned aerial vehicle (UAV).

[0006] To solve the above technical problems, the present invention adopts the following technical solution: The present invention provides a multi-axis unmanned aerial vehicle, including a fuselage and a frame. The frame includes a set of support legs symmetrically arranged on the lower side of the fuselage. Each support leg includes a vertical pole and a horizontal bar arranged at the lower end of the vertical pole. The distance between the lower ends of the vertical poles in the two sets of support legs is greater than the distance between the upper ends.

[0007] A clamping assembly is provided on the outside of the upright, and a lifting assembly for driving the clamping assembly to move up and down is provided inside the upright;

[0008] The lifting assembly includes a lifting screw and a lifting ring that cooperates with the lifting screw;

[0009] The lifting screw is rotatably equipped with bearings at both ends;

[0010] A fixing rod is provided between the lifting ring and the clamping assembly, and the upright has a pre-set clearance groove for the fixing rod to move.

[0011] Preferably, the clamping assembly includes a support plate and a pressing portion fixed to the upper side of the support plate.

[0012] Preferably, the extrusion section includes a pair of side pressure strips and a middle pressure strip connected between the side pressure strips, and the two extrusion sections are arranged opposite each other on the side where the opening is formed.

[0013] Preferably, a snap-fit ​​groove is reserved between the lower side of the opposite side of the two medium-pressure edge strips and the support plate.

[0014] Preferably, the upright includes a fixed tube and a lifting tube, wherein the upper end of the lifting tube is slidably sleeved on the lower end of the fixed tube;

[0015] The lifting screw includes an upper rod and a lower rod. The upper rod is coaxially rotatably disposed in a fixed tube, and the lower rod is coaxially rotatably disposed in a lifting tube. The lower end of the upper rod is provided with an upper mating key, and the upper end of the lower rod is provided with a lower mating key.

[0016] When the upper mating key contacts the lower mating key, the upper and lower locking rods rotate synchronously and coaxially.

[0017] Preferably, an abutment ring is coaxially fixed to the outer side of the fixed tube, an upper support ring is coaxially arranged on the inner side of the upper end of the lifting tube, a lower support ring is coaxially arranged inside the lifting tube, the abutment ring is located between the upper support ring and the lower support ring, and an elastic element is arranged between the abutment ring and the lower support ring.

[0018] Preferably, the upper mating key is a U-shaped block with its opening facing downwards, and the lower mating key is a long strip block that slides in and out of the U-shaped block;

[0019] When the upper support ring contacts the abutment ring, the lower mating key completely disengages from the upper mating key.

[0020] Preferably, the upper end of the lifting screw extends into the machine body and is coaxially fixed with a transmission wheel, and a synchronous belt is provided between the transmission wheels on the parallel lifting screw.

[0021] Preferably, a driven gear is coaxially fixed on a pair of lifting screws with opposite inclination directions, and a motor and a set of driving gears are provided in the frame.

[0022] Preferably, the drive gear set includes a power gear fixed to the output end of the motor and a reduction gear located between the power gear and the driven gear.

[0023] The beneficial effects of this invention are as follows:

[0024] 1. The frame under the drone is equipped with electrically controlled clamping components, which enable quick assembly and disassembly of different additional equipment;

[0025] 2. The lifting screw structure of the control clamping component is combined with the support foot to form a landing buffer for the drone and a position locking function for the clamping component. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the embodiments of the present invention 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 some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0027] Figure 1 This is a structural schematic diagram of a multi-axis unmanned aerial vehicle (UAV) provided in an embodiment of the present invention.

[0028] Figure 2 This is mainly used to demonstrate the power structure in the fuselage that drives the lifting screw.

[0029] Figure 3 This is a half-section diagram of the upright, mainly used to illustrate the internal structure of the upright.

[0030] Figure 4 This is a structural diagram mainly used to illustrate the detachable joint between the upper and lower rods.

[0031] Explanation of reference numerals in the attached drawings: 1. Machine body; 2. Machine frame; 3. Support leg; 4. Upright pole; 41. Fixing tube; 411. Support ring; 42. Lifting tube; 43. Abutment ring; 5. Crossbar; 6. Lifting screw; 7. Upper rod; 71. Upper mating key; 72. Transmission wheel; 73. Synchronous belt; 74. Driven gear; 8. Lower rod; 81. Lower mating key; 9. Lifting ring; 91. Fixing rod; 10. Clamping assembly; 11. Support plate; 12. Extrusion section; 13. Motor; 14. Power gear; 15. Reduction gear. Detailed Implementation

[0032] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0033] Figure 1-4 As shown, the present invention provides a multi-rotor drone, including an upper fuselage 1 and a lower frame 2. Different additional equipment can be mounted on the drone through the lower frame 2 and mounting bracket to enable operation in different environments.

[0034] Since mounting brackets for different loads vary in size, this application aims to provide a mounting structure that can accommodate various additional devices with a wider range of applications.

[0035] The frame 2 includes a set of support legs 3 symmetrically installed below the body 1. Each support leg 3 includes a pair of parallel uprights 4. A horizontal crossbar 5 is fixedly installed at the lower end of the uprights 4 in the same set of support legs 3. The distance between the upper ends of the uprights 4 in the two sets of support legs 3 is smaller than the distance between the lower ends. In addition, a lifting screw 6 is rotatably installed in the uprights 4. Multiple bearings are provided in the uprights 4 to support the rotation of the lifting screw 6. A lifting ring 9 is also threaded on the lifting screw 6. A fixing rod 91 extends horizontally outward from the lifting ring 9 and is mounted on the fixing rod 91. A clamping assembly 10 is installed on the fixing rod 91. The uprights 4 are also pre-set with a clearance groove to avoid the vertical movement of the fixing rod 91.

[0036] When additional equipment is configured under the multi-rotor drone, since the different additional equipment has different hoisting heights under the multi-rotor drone, a mounting plate is preset on the top of the additional equipment, and the mounting plate needs to be placed between the clamping components 10.

[0037] If the opening and closing distance of the clamping component 10 is less than the space required by the mounting plate, then rotate the lifting screw 6 to make the lifting ring 9 move downward, that is, the opening and closing distance between the clamping components 10 increases to the point that the mounting plate can be fully placed.

[0038] Then, the lifting screw 6 is rotated in the opposite direction, causing the lifting ring 9 to move upward. At this time, the opening and closing distance between the clamping components 10 is reduced until the clamping components 10 can fully clamp the mounting plate. Therefore, it is only necessary to design mounting plates of different sizes to adapt to the additional accessories of different heights in advance, so that it can be quickly fixed and disassembled under the multi-axis drone.

[0039] The clamping assembly 10 mentioned above includes a support plate 11 and a pressing part 12. The pressing part 12 is fixedly installed on the upper side of the support plate 11. Specifically, the pressing part 12 includes a pair of side pressing strips and a middle pressing strip. The two ends of the middle pressing strip are fixedly connected to the side pressing strips respectively. The middle pressing strip and the two side pressing strips form a U-shaped structure, and a snap-fit ​​groove is reserved between the lower side of the opposite side of the two middle pressing strips and the support plate 11.

[0040] During the installation of the auxiliary equipment, the mounting plate is placed on the support plate 11 between the two clamping components 10. During the process of fixing the auxiliary equipment, the clamping components 10 move relative to each other until one end of the mounting plate is embedded in the snap-fit ​​groove, which limits the mounting plate in the horizontal and vertical directions and realizes the stable installation of the auxiliary equipment.

[0041] Furthermore, the top of the lifting screw 6 extends into the body 1. Inside the body 1, a power assembly for driving the lifting screw 6 to rotate is provided. The power assembly includes a transmission wheel 72 coaxially mounted on the lifting screw 6. The transmission wheels 72 on the lifting screw 6 in the same group of support feet 3 are connected by a transmission belt. A driven gear 74 is coaxially mounted on each lifting screw 6 in different groups of support feet 3. Inside the body 1 and located between the two driven gears 74, a drive gear set is provided. The drive gear set includes a power gear 14 and two reduction gears 15. The power gear 14, reduction gears 15, and driven gears 74 mesh sequentially. A motor 13 for driving the power gear 14 is provided on the lower outer side of the body 1. Through the motor 13 and the transmission structure inside the body 1, the forward and reverse rotation of the four lifting screws 6 can be quickly driven, i.e., the dynamic control of the clamping assembly 10.

[0042] However, in actual operation, due to the unavoidable slight vibrations during the flight of the UAV, the vibration-guided gear 14 is prone to rotation, which may cause the clamping assembly 10 to loosen. To solve this problem, in this application, the lifting screw 6 adopts a segmented structure, dividing the lifting screw 6 into an upper rod 7 and a lower rod 8, while the upright rod 4 is divided into a fixed tube 41 and a lifting tube 42.

[0043] The upper end of the fixed tube 41 is installed on the lower side of the machine body 1, and the lower end of the fixed tube 41 is slidably inserted into the lifting tube 42. The upper rod 7 is coaxially rotatably installed in the fixed tube 41, and the lower rod 8 is coaxially rotatably installed in the lifting tube 42. An upper mating key 71 is provided at the lower end of the upper rod 7, and a lower mating key 81 is provided at the upper end of the lower rod 8. By moving the lifting tube 42, the upper mating key 71 and the lower mating key 81 can be joined and separated. When the upper mating key 71 and the lower mating key 81 are separated, the synchronous rotation control of the four lifting screws 6 by the power gear 14 is disconnected, thus preventing the clamping assembly 10 from loosening.

[0044] The fixed tube 41 mentioned above extends into the lifting tube 42 and is coaxially fixed with an abutment ring 43 on its outer side. Support rings 411 are provided inside the lifting tube 42 and at its upper end. The upper support ring 411 is installed in the lifting tube 42 by means of a threaded connection. At the same time, an elastic element is provided between the abutment ring 43 and the lower support ring 411. The elastic element is the support ring 411.

[0045] When the drone is placed on the ground and lands, the support spring is compressed, reducing the impact force when the drone lands. At the same time, the lower rod 8 moves upward with the lifting tube 42, so that the lower mating key 81 and the upper mating key 71 are engaged and connected, and the clamping assembly 10 can be electrically controlled by the motor 13 to clamp and loosen.

[0046] After the drone takes off, the support spring acts on the abutment ring 43 and the support ring 411, causing the lower rod 8 to move down with the lifting tube 42, and the lower mating key 81 to separate from the upper mating key 71. This effectively prevents the clamping assembly 10 from loosening due to the vibration of the fuselage 1, and improves the installation stability of the auxiliary equipment.

[0047] The working principle of this invention is:

[0048] When attaching an auxiliary device to the bottom of the drone, start motor 13 to control the clamping assembly 10 to separate, then place the mounting plate on top of the auxiliary device between the two clamping assemblies 10, and finally control the clamping assembly 10 to move relative to each other until the clamping assembly 10 completely fixes the mounting plate, thus achieving quick assembly and disassembly of the auxiliary device.

[0049] After the drone takes off, the lower rod 8 of the lifting screw 6 moves down, causing the upper mating part and the lower mating key 81 to separate, thereby preventing vibration from causing the four lifting screws 6 to rotate synchronously in the same direction and ensuring the clamping stability of the clamping assembly 10.

[0050] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A multi-rotor unmanned aerial vehicle (UAV), comprising a fuselage (1) and a frame (2), characterized in that, The frame (2) includes a set of support legs (3) symmetrically arranged on the lower side of the body (1). The support legs (3) include uprights (4) and crossbars (5) arranged at the lower end of the uprights (4). The distance between the lower ends of the uprights (4) in the two sets of support legs (3) is greater than the distance between the upper ends. A clamping assembly (10) is provided on the outside of the upright (4), and a lifting assembly for driving the clamping assembly (10) to move up and down is provided inside the upright (4). The lifting assembly includes a lifting screw (6) and a lifting ring (9) that cooperates with the lifting screw (6); The lifting screw (6) is rotatably equipped with bearings at both ends; A fixing rod (91) is provided between the lifting ring (9) and the clamping assembly (10), and a clearance groove for the fixing rod (91) to move is preset on the upright (4); The upright (4) includes a fixed tube (41) and a lifting tube (42), with the upper end of the lifting tube (42) slidably sleeved on the lower end of the fixed tube (41); The lifting screw (6) includes an upper rod (7) and a lower rod (8). The upper rod (7) is coaxially rotatably disposed in the fixed tube (41), and the lower rod (8) is coaxially rotatably disposed in the lifting tube (42). The lower end of the upper rod (7) is provided with an upper mating key (71), and the upper end of the lower rod (8) is provided with a lower mating key (81). When the upper mating key (71) contacts the lower mating key (81), the upper rod (7) and the lower rod (8) are locked to rotate synchronously and coaxially. An abutment ring (43) is coaxially fixed on the outer side of the fixed tube (41), an upper support ring (411) is coaxially provided on the inner side of the upper end of the lifting tube (42), a lower support ring (411) is coaxially provided inside the lifting tube (42), the abutment ring (43) is located between the upper support ring (411) and the lower support ring (411), and an elastic element is provided between the abutment ring (43) and the lower support ring (411); The upper end of the lifting screw (6) extends into the machine body (1) and is coaxially fixed with a transmission wheel (72). A synchronous belt (73) is provided between the transmission wheels (72) on the parallel lifting screw (6).

2. A multi-rotor unmanned aerial vehicle as described in claim 1, characterized in that, The clamping assembly (10) includes a support plate (11) and a pressing part (12) fixed to the upper side of the support plate (11).

3. A multi-rotor unmanned aerial vehicle as described in claim 2, characterized in that, The extrusion section (12) includes a pair of side pressure strips and a middle pressure strip connected between the side pressure strips, and the two extrusion sections (12) are arranged opposite each other on the side where they form an opening.

4. A multi-rotor unmanned aerial vehicle as described in claim 3, characterized in that, A snap-fit ​​groove is reserved between the lower side of the opposite side of the two medium-pressure edge strips and the support plate (11).

5. A multi-rotor unmanned aerial vehicle as described in claim 1, characterized in that, The upper mating key (71) is a U-shaped block with the opening facing downwards, and the lower mating key (81) is a long strip block that slides in and out of the U-shaped block; When the upper support ring (411) contacts the abutment ring (43), the lower mating key (81) completely disengages from the upper mating key (71).

6. A multi-rotor unmanned aerial vehicle as described in claim 1, characterized in that, One of the pair of lifting screws (6) with opposite tilt directions is coaxially fixed with driven gears (74), and the frame (2) is equipped with a motor (13) and a set of driving gears.

7. A multi-rotor unmanned aerial vehicle as described in claim 6, characterized in that, The active gear set includes a power gear (14) fixed to the output end of the motor (13) and a reduction gear (15) located between the power gear (14) and the driven gear (74).

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