Unmanned aerial vehicle beam rotation mechanism

Description

[0001] FIELD OF TECHNOLOGY

[0002] This utility model relates to aviation, specifically to a beam-rotating mechanism for an unmanned aerial vehicle (UAV). The utility model can be used in multi-rotor UAVs, for example, for spraying liquid or solid crop protection products and fertilizers, transporting and automatically dropping payloads, as an aerial loudspeaker, etc.

[0003] STATE OF THE ART

[0004] A known technical solution involves multicopter arms rotating around a vertical axis located at their inner ends and being secured in the deployed position using elastic nylon clips. This mechanism is used in multicopter frames manufactured by the Chinese company Tarot. However, the elastic clip does not prevent torsional and compression-tension loads on the arm, and can also lose elasticity and break at low ambient temperatures.

[0005] Patent RU 188461 U1, published April 15, 2019, class B64C 27 / 08, describes a multicopter in which the arms can rotate around a vertical axis located at their inner ends and are locked in the deployed position using a sliding U-shaped bracket and spring-loaded pins. However, this design is complex to manufacture; in particular, it requires precision drilling of the arm tubes, which can also negatively impact their strength. Furthermore, the use of extendable arms can introduce play in the structure, making it difficult to precisely balance the drone's motors.

[0006] From patent RU 210795 U1, published 05.05.2022, cl. B64C 27 / 08, B64C 39 / 02, a mechanism for folding the beams of a multicopter is known, consisting of a tip mounted on the inner end of the beam, freely rotating around a vertical axis, as well as an engagement group, which in turn is a clamp capable of being rigidly fixed on the beam with two mechanical dovetail connectors curved along an arc and fixed parts of the engagement group rigidly fixed on the body of the drone, having a mating part of a mechanical dovetail connector curved along an arc, located in such a way that when the beam is deployed, the detachable parts of the clamp are inserted into the mating parts of the fixed parts, while the parts of the engagement group have coaxial holes that allow the beam to be fixed in the open position using an annular cotter pin. However, this folding mechanism requires precise alignment of the beams on the vertical axis, which complicates the assembly process.

[0007] The closest analogue is patent KR 102009515 B1, published 09.08.2019, class B64C 1 / 30, B64C 27 / 08, B64C 27 / 12, B64C 39 / 02, which discloses a foldable UAV. The foldable UAV comprises a lower body part, an upper body part mounted on the lower body part with the ability to rotate around an axis of rotation perpendicular to the ground; a rotation limiting means for limiting the rotation range between the lower body part and the upper body part. Beams with propeller-motor groups are attached to the upper and lower body parts. The upper body and the lower body are cylindrical in shape and have the same diameter. A rotating shaft is installed in the center of the upper body, connected to the lower body. A bearing is installed on the outer surface of the rotating shaft to allow rotation of the upper body relative to the lower body.In order for the upper housing to rotate stably relative to the lower housing, a disc-shaped rotating part protrudes downward from the lower surface of the upper housing, and a circular rotating part is formed in the lower housing, containing a groove into which the disc-shaped rotating part is rotatably inserted.

[0008] However, the known design of the UAV folding mechanism requires the bearing to be mounted on the shaft, which complicates the assembly due to the need for precise alignment of the shaft and bearing; misalignment can lead to jamming and breakage of the folding mechanism.

[0009] The technical problem is to eliminate the above defect.

[0010] Disclosure of the essence of the utility model

[0011] The technical problem solved by the utility model consists of developing a mechanism for rotating the beam of an unmanned aerial vehicle, devoid of the drawbacks of the closest analogue.

[0012] The technical result achieved by the utility model consists in increasing the reliability and failure-free operation of the UAV beam rotation mechanism.

[0013] The above technical result is achieved by means of a mechanism for rotating the beam of an unmanned aerial vehicle, comprising a hub, a bracket, a clamp, a bearing, wherein the bracket is designed with the possibility of installing one beam, and the hub with the possibility of installing another beam of the unmanned aerial vehicle coaxially in different horizontal planes, wherein the bearing is located on the bracket and is attached to the bracket using a clamp, wherein the clamp rigidly fixes the inner ring of the bearing, and the hub is mounted on the outer ring of the bearing with the possibility of rotating the bracket relative to the hub.

[0014] Increased reliability and trouble-free operation of the UAV beam rotation mechanism are achieved through the use of a clamp to maintain coaxiality during operation of the beam rotation mechanism.

[0015] In one embodiment of the beam rotation mechanism, the bearing is a ball bearing.

[0016] In another embodiment of the beam rotation mechanism, the bearing is a radial thrust bearing.

[0017] In another embodiment of the beam rotation mechanism, the bearing is fastened to the bracket using a clamp by means of a screw connection.

[0018] In another embodiment of the beam rotation mechanism, the bearing is fastened to the bracket using a clamp using four screws.

[0019] In another embodiment of the beam rotation mechanism, the hub is designed with the possibility of attaching a platform for avionics and a battery platform.

[0020] In another embodiment of the beam rotation mechanism, the bracket is designed with the possibility of attaching a removable payload module.

[0021] In another embodiment, the beam rotation mechanism is designed to be installed in the body of an unmanned aerial vehicle.

[0022] In another embodiment, the unmanned aerial vehicle is a quadcopter.

[0023] In another embodiment, the quadcopter has a “Quad+” configuration.

[0024] Brief description of drawings

[0025] The utility model will be more understandable from the description, which is not limiting in nature and is given with reference to the figures of drawings 1-15 and a three-dimensional model of the mechanism for rotating the UAV beam in the flight position according to the utility model.

[0026] Fig. 1 illustrates a general view of the UAV beam rotation mechanism in the flight position according to the utility model.

[0027] Fig. 2 illustrates a left view of the UAV beam rotation mechanism in the flight position according to the utility model.

[0028] Fig. 3 illustrates a top view of the UAV beam rotation mechanism in the flight position according to the utility model.

[0029] Fig. 4 illustrates a sectional view A-A of the UAV beam rotation mechanism in the flight position according to the utility model.

[0030] Fig. 5 illustrates a general view of the hub of the UAV beam rotation mechanism according to the utility model.

[0031] Fig. 6 illustrates a top view of the hub of the UAV beam rotation mechanism according to the utility model.

[0032] Fig. 7a, 7b and 7c illustrate views A-A, B-B and B-B of the hub of the UAV beam rotation mechanism according to the utility model.

[0033] Fig. 8 illustrates a general view of the bracket of the UAV beam rotation mechanism according to the utility model.

[0034] Fig. 9 illustrates a top view of the bracket of the UAV beam rotation mechanism according to the utility model.

[0035] Fig. 10a and 10b illustrate views A-A and B-B of the bracket of the UAV beam rotation mechanism according to the utility model.

[0036] Fig. 11 illustrates a bottom view B of the bracket of the UAV beam rotation mechanism according to the utility model.

[0037] Fig. 12 illustrates top and left views of the clamp of the UAV beam rotation mechanism according to the utility model.

[0038] Fig. 13 illustrates the beam rotation mechanism of the UAV with a platform for avionics according to the utility model.

[0039] Fig. 14 illustrates an example of installing a beam rotation mechanism in a UAV according to the utility model.

[0040] Fig. 15 illustrates a general view of the UAV with a beam rotation mechanism in the transport position according to the utility model.

[0041] The following are indicated on the figures of the drawings: 1 - hub; 2 - bracket; 3 - clamp; 4 - screw; 5 - nut; 6 - ring; 7 - washer; 8 - bearing; 9 - housing; 10 - fixed beam with propeller-motor groups; 11 - rotating beam with propeller-motor groups; 12 - beam rotation mechanism with avionics platform; 13 - symmetrically located lugs in the housing wall; 14 - means of fastening and locking the rotating beam; 15 - battery; 16 - battery platform; 17 - housing cover.

[0042] Implementation of a utility model

[0043] This utility model relates to designs of a beam rotation mechanism for multi-rotor unmanned aerial vehicles with vertical takeoff and landing (multicopters). The multicopter comprises four rotor groups with electric motor controllers, a flight controller, a sensor system for monitoring and flight control, and a beam rotation mechanism that ensures the unmanned aerial vehicle's compactness and ease of transportation. The beam rotation is performed along the aircraft's flight axis.

[0044] The unmanned aerial vehicle (UAV) beam rotation mechanism according to this utility model comprises a hub, a bracket, a clamp, and a bearing. The bracket is configured to mount one arm, and the hub is configured to mount the other arm of the UAV coaxially in different horizontal planes. The bearing is mounted on the bracket and secured to the bracket using a clamp. The clamp securely holds the inner bearing ring, and the hub is mounted on the outer bearing ring, allowing the bracket to rotate relative to the hub. The bearing is a radial-thrust ball bearing. The bearing is secured to the bracket using a clamp via a screw connection using four screws. The beam rotates along the aircraft's flight axis. The rotation mechanism ensures compactness and ease of transportation of the UAV.Increased reliability and trouble-free operation of the UAV beam rotation mechanism are achieved through the use of a clamp to maintain coaxiality during operation of the beam rotation mechanism.

[0045] Fig. 1-4 show the beam rotation mechanism in the assembled flight position. The UAV beam rotation mechanism comprises a hub 1 (Fig. 5-7), a bracket 2 (Fig. 8-11), a clamp 3 (Fig. 12), and a bearing 8 (for example, an NSK 7909A5 radial thrust ball bearing). The bearing 8 is mounted on the bracket 2 and is secured to the bracket 2 using the clamp 3, and the clamp 3 rigidly fixes the inner ring of the bearing 8, while the hub 1 is mounted on the outer ring of the bearing 8 with the possibility of rotating the bracket 2 relative to the hub 1. The bearing 8 is secured to the bracket 2 using the clamp 3 by means of four screw connections. Each screw connection comprises a screw 4, a nut 5, a ring 6, and a washer 7.

[0046] The hub contains three places for mounting the avionics platform (Fig. 7b) and four places for mounting the battery platform (Fig. 7a).

[0047] The bracket has four mounting locations for the clamp 3 (Fig. 10b) and four mounting locations for the payload (Fig. 10a). The payload is, for example, in the form of a removable module. The removable module is, for example, a system for spraying liquid plant protection products and fertilizers, a system for dispersing solid plant protection products and fertilizers, a discharge system, or a loudspeaker.

[0048] The process of assembling the beam turning mechanism according to the present utility model includes: installing the NSK 7909A5 bearing into the hub 1 using a hydraulic press (before pressing, grease is applied to the outer surface of the bearing), installing the ring into the mounting groove of the hub 1 using a ring puller, installing the hub 1 with the bearing 8 and the ring onto the bracket 2 (before installation, grease is applied to the inner surface of the bearing 8 and the mounting location), installing the clamp 3 and fastening it using fasteners 4, 5, 6, 7.

[0049] The beam rotation mechanism according to the present utility model is designed for installation in the body of an unmanned aerial vehicle, for example, a quadcopter with the "Quad+" configuration (Fig. 14). The quadcopter comprises a hollow body (9) made in the form of a cylindrical tube. Inside the body (9) there is a beam rotation mechanism with an avionics platform (12). A fixed beam (10) with propeller-motor groups directed with screws upwards is secured to the hub (1), and a rotating beam (11) with propeller-motor groups directed with screws downwards is secured to the bracket (2). In the wall of the hollow body (9) at the intersection of the wall of the body (9) with the horizontal plane in which the beam (11) rotates, two symmetrically located lugs (13) are made along the beam rotation trajectory. The rotating beam is equipped with means for fastening and securing the rotating beam (14) in the form of aluminum screw nuts.On the housing (9) are mounted fixed parts of the engagement group, having a mating part for fastening screw nuts. In the upper part inside the hollow housing (9) above the beam rotation mechanism (12) is a power unit in the form of two storage batteries (15) installed on the platform (16). From above, the housing is closed with a cover (17). The rotation of the beam (11) is carried out due to the rotation mechanism (12), which ensures compactness and ease of transportation of the unmanned aerial vehicle. During deployment, the operator places the aircraft horizontally on the ground or other hard surface, after which he rotates the beam (11) about its axis in the horizontal plane, bringing it to the flight position (Fig. 14). Then the operator fixes the position of the beam (11) using aluminum screw nuts (14). To fold and transfer the aircraft to the transport position (Fig.15, 16) the operator performs these actions in reverse order: unscrews the nuts (14) and rotates the beam (11) in the opposite direction, then fixes the beam (11) in the transport position using the nuts.

[0050] The utility model is disclosed above with reference to a specific embodiment. Other embodiments of the present utility model are also obvious, without changing its essence as disclosed in the above description.

[0051] The detailed description of the utility model includes numerous implementation details intended to provide a clear understanding of the present utility model. However, it is obvious to those skilled in the art how the present utility model can be used, both with and without these implementation details.

Claims

1. A mechanism for turning the beam of an unmanned aerial vehicle, comprising a hub (1), a bracket (2), a bearing (8), wherein the bracket (2) is configured to install one beam, and the hub (1) is configured to install another beam of the unmanned aerial vehicle coaxially in different horizontal planes, characterized in that it comprises a clamp (3), wherein the bearing (8) is located on the bracket (2) and is attached to the bracket (2) using the clamp (3), wherein the clamp (3) rigidly fixes the inner ring of the bearing (8), and the hub (1) is mounted on the outer ring of the bearing (8) with the possibility of rotating the bracket (2) relative to the hub (1).

2. The beam rotation mechanism according to paragraph 1, characterized in that the bearing (8) is a ball bearing.

3. The beam rotation mechanism according to paragraph 1, characterized in that the bearing (8) is a radial thrust bearing.

4. The beam rotation mechanism according to paragraph 1, characterized in that the fastening of the bearing (8) to the bracket (2) using the clamp (3) is carried out by means of a screw connection.

5. The beam rotation mechanism according to paragraph 1, characterized in that the fastening of the bearing (8) to the bracket (2) using the clamp (3) is carried out by means of four screws.

6. The beam rotation mechanism according to paragraph 1, characterized in that the hub (1) is designed with the possibility of attaching a platform for avionics and a battery platform.

7. The beam rotation mechanism according to claim 1, characterized in that the bracket (2) is designed with the possibility of attaching a removable payload module.

8. The beam rotation mechanism according to paragraph 1, characterized in that it is designed with the possibility of installation in the body of an unmanned aerial vehicle.

9. The beam rotation mechanism according to paragraph 1, characterized in that the unmanned aerial vehicle is a quadcopter.

10. The beam rotation mechanism according to paragraph 9, characterized in that the quadcopter has a “Quad+” configuration.

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