Unmanned aerial vehicle with a beam-rotating mechanism

Abstract

The invention relates to aviation, specifically to unmanned aerial vehicles with a beam-rotating mechanism. The unmanned aerial vehicle comprises a body, two arms with propeller-motor assemblies, and a beam-rotating mechanism. The two arms and the beam-rotating mechanism are mounted coaxially and the arms are located in different horizontal planes. One arm is fixed and is rigidly attached to the beam-rotating mechanism, while the other arm is rotatable and is attached to the beam-rotating mechanism with the ability to rotate the beam in a horizontal plane around its axis. The body is hollow, and the beam-rotating mechanism is located within the hollow body. Two symmetrically located eyes are formed in the wall of the hollow body at the intersection of the wall of the body with the horizontal plane in which the beam rotates, along the beam-rotating trajectory. The technical result consists in reducing the weight of the unmanned aerial vehicle, which is foldable for transportation.

Description

[0001] FIELD OF TECHNOLOGY

[0002] This utility model relates to aviation, specifically to unmanned aerial vehicles with a beam-steering mechanism. This utility model can be used, at a minimum, for spraying liquid or dispersing solid crop protection products and fertilizers, transporting and automatically dropping payloads, as an airborne loudspeaker, and so on.

[0003] STATE OF THE ART

[0004] From patent US 10035597 B2, published 31.07.2018, cl. B64C 1 / 30, B64C 39 / 02, B64D 1 / 08, B64D 17 / 80, B64C 25 / 00, an unmanned aerial system (UAS) is known, including a multicopter with the possibility of placement in a cylindrical housing (SDM) in a compact configuration, having a plurality of propeller-motor groups, a plurality of elongated arms and a central rotating device. Each elongated arm comprises at least one propeller-motor group. The central rotating device supports a plurality of elongated arms radially extending from the central rotating device. Rotational movement of the first support structure of the central rotating device relative to the second support structure of the central rotating device leads to synchronous rotation of the first pair of elongated arms relative to the second pair of elongated arms. The rotational movement is aimed at converting the multicopter from a compact transport configuration to a flight configuration.

[0005] 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 known 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 mounted in the center of the upper body and connected to the lower body. A bearing is mounted 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.

[0006] However, the known folding UAV design requires mounting the bearing on the shaft, which complicates assembly due to the need for precise shaft and bearing alignment. Furthermore, the upper and lower body parts are massive, which, along with the shaft, increases the UAV's weight. The massive body design prevents the placement of avionics, batteries, and other components.

[0007] The technical problem is to eliminate the above mentioned shortcomings.

[0008] DISCLOSURE OF THE ESSENCE OF THE UTILITY MODEL

[0009] The technical problem solved by this utility model consists of developing a foldable, lightweight UAV of simple assembly with the possibility of placing the main components of the UAV inside the body.

[0010] The technical result achieved by the present utility model is to reduce the weight of the UAV, which is designed to be foldable for transportation.

[0011] The above technical result is achieved by an unmanned aerial vehicle comprising a body, two beams with propeller-motor groups, a beam rotation mechanism, wherein the two beams and the beam rotation mechanism are installed coaxially and the beams are located in different horizontal planes, one beam is fixed and is fixedly attached to the beam rotation mechanism, the other beam is rotary and is attached to the beam rotation mechanism with the ability to rotate the beam in a horizontal plane around its axis, characterized in that the body is hollow, wherein the beam rotation mechanism is located inside the hollow body, wherein in the wall of the hollow body at the intersection of the wall of the body with the horizontal plane in which the beam rotation is carried out, along the trajectory of the beam rotation, two symmetrically located eyes are made.

[0012] The UAV's weight is reduced by a hollow body with symmetrical lugs embedded in its walls. This allows for a lighter body and allows for the beam rotation mechanism, power plant, and avionics to be housed within the body, eliminating the need for a landing gear, further reducing the UAV's weight.

[0013] In one embodiment of the unmanned aerial vehicle, the beam rotation mechanism comprises a hub, a bracket, a ball bearing and a clamp, wherein the ball bearing is located on the bracket and is rigidly attached to the bracket using a clamp, and the hub is mounted on the ball bearing with the ability to rotate the bracket relative to the hub.

[0014] In another embodiment of the unmanned aerial vehicle, the fixed beam is fixedly attached to the hub, and the rotating beam is fixedly attached to the bracket of the beam rotating mechanism.

[0015] In another embodiment of the unmanned aerial vehicle, means for securing and fixing the rotating beam are provided on the rotating beam and on the body with the possibility of securing and fixing the rotating beam in the flight position or in the transport position.

[0016] In another embodiment of the unmanned aerial vehicle, the means for securing and fixing the rotating beam are made of an aluminum alloy.

[0017] In another embodiment of the unmanned aerial vehicle, the means for securing and fixing the rotating beam are made of thermoplastic polymers.

[0018] In another embodiment of the unmanned aerial vehicle, the fastening means are screw nuts secured to the rotating beam, and counter parts for fastening the screw nuts, made in the body.

[0019] In another embodiment of the unmanned aerial vehicle, the unmanned aerial vehicle is a quadcopter with a “Quad+” configuration.

[0020] In another embodiment of the unmanned aerial vehicle, the propellers of the propeller-motor groups on the fixed beam are directed upward, and the propellers of the propeller-motor groups on the rotating beam are directed downward.

[0021] In another embodiment of the unmanned aerial vehicle, the power plant and avionics are located inside the body.

[0022] In another embodiment of the unmanned aerial vehicle, the body is made in the form of a cylindrical tube.

[0023] In another embodiment of the unmanned aerial vehicle, the body is made of composite materials.

[0024] In another embodiment of the unmanned aerial vehicle, a payload in the form of at least one removable module is located inside the body.

[0025] In another embodiment of the unmanned aerial vehicle, the removable module is at least a system for spraying liquid plant protection products and fertilizers, a system for scattering solid plant protection products and fertilizers, a discharge system, and a loudspeaker.

[0026] In another embodiment of the unmanned aerial vehicle, the unmanned aerial vehicle comprises a removable chassis, while the body is shortened.

[0027] BRIEF DESCRIPTION OF DRAWINGS

[0028] 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 1-12 and a three-dimensional model of the UAV with a mechanism for rotating the beam in the flight position according to this utility model.

[0029] Fig. 1 illustrates a general view of a UAV with a beam rotation mechanism in a flight position according to the present utility model.

[0030] Fig. 2 illustrates a left view of a UAV with a beam rotation mechanism in a flight position according to the present utility model.

[0031] Fig. 3 illustrates a top view of a UAV with a beam rotation mechanism in a flight position according to the present utility model.

[0032] Fig. 4 illustrates a general view of the UAV with a beam rotation mechanism in the transport position according to the present utility model.

[0033] Fig. 5 illustrates a left view of a UAV with a beam rotation mechanism in the transport position according to the present utility model.

[0034] Fig. 6 illustrates a top view of a UAV with a beam rotation mechanism in the transport position according to the present utility model.

[0035] Fig. 7 illustrates a general view of the UAV beam rotation mechanism in the flight position according to the present utility model.

[0036] Fig. 8 illustrates a left view of the UAV beam rotation mechanism in the flight position according to the present utility model.

[0037] Fig. 9 illustrates a top view of the UAV beam rotation mechanism in the flight position according to the present utility model.

[0038] Fig. 10 illustrates a sectional view A-A of the UAV beam rotation mechanism in the flight position according to the present utility model.

[0039] Fig. 11 illustrates a beam rotation mechanism of a UAV with an avionics platform according to the present utility model.

[0040] Fig. 12 illustrates an example of the implementation of a UAV with a beam rotation mechanism according to the present 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 the design of 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 compactness and ease of transportation of the unmanned aerial vehicle. The beam rotation is carried out along the aircraft's flight axis.

[0044] The unmanned aerial vehicle according to this utility model comprises a hollow body, two arms with propeller-motor assemblies, and a beam rotation mechanism. The body may be designed as a cylindrical tube made of composite materials. The two arms and the beam rotation mechanism are mounted coaxially, and the arms are located in different horizontal planes. One arm is fixed and is rigidly attached to the beam rotation mechanism, while the other arm is rotatable and is attached to the beam rotation mechanism with the ability to rotate the arm in the horizontal plane around its axis. The beam rotation mechanism is located within the hollow body, and in the wall of the hollow body, at the intersection of the wall of the body with the horizontal plane in which the beam rotates, two symmetrically located eyes are formed along the beam rotation trajectory.The beam rotation mechanism comprises a hub, a bracket, a ball bearing, and a clamp. The ball bearing is located on the bracket and is rigidly attached to the bracket using the clamp, while the hub is mounted on the ball bearing so that the bracket can rotate relative to the hub. The fixed beam is rigidly attached to the hub, and the rotating beam is rigidly attached to the beam rotation mechanism bracket. Attachments for securing and securing the rotating beam are provided on the rotating beam and on the housing, allowing the rotating beam to be secured and secured in the flight position or in the transport position. The attachments may comprise screw nuts secured to the rotating beam and mating parts for securing the screw nuts, formed in the housing. The attachments for securing and securing the rotating beam may be made, for example, of an aluminum alloy or thermoplastic polymers.The propellers of the fixed-wing propeller assemblies point upward, while the propellers of the rotating-wing propeller assemblies point downward. The hollow body also houses the propulsion system, flight controller, and avionics suite. The unmanned aerial vehicle may contain a payload in the form of at least one removable module. The removable module is located within the body and comprises at least one system for spraying liquid plant protection products and fertilizers, a system for dispersing solid plant protection products and fertilizers, a release system, and a loudspeaker.

[0045] Fig. 1, Fig. 2, Fig. 3 show a UAV with a beam rotation mechanism in the flight position, and Fig. 4, Fig. 5, Fig. 6 - in the transport position, according to the present utility model. The UAV is a quadcopter with a "Quad+" configuration.

[0046] The mechanism for turning the beam of an unmanned aerial vehicle (Fig. 7, Fig. 8, Fig. 9, Fig. 10, Fig. 11, Fig. 12) comprises a hub 1, a bracket 2, a clamp 3, and a bearing 8. Bracket 2 is configured to mount one beam, and the hub 1 is configured to mount another beam of the unmanned aerial vehicle coaxially in different horizontal planes. Bearing 8 is located on bracket 2 and is attached to bracket 2 using clamp 3, and clamp 3 rigidly fixes the inner ring of bearing 8, while hub 1 is mounted on the outer ring of bearing 8 with the ability to rotate bracket 2 relative to hub 1. Bearing 8 is a ball radial thrust bearing (for example, an NSK 7909A5 bearing). The fastening of the bearing 8 to the bracket 2 with the help of the clamp 3 is carried out by means of four screw connections. Each screw connection contains a screw 4, a nut 5, a ring 6, a washer 7. The hub 1 contains three places for fastening the platform for the avionics (Fig.11) and four mounting locations for the battery platform (Fig. 12). The bracket contains four mounting locations for the clamp 3 and four mounting locations for the payload (Fig. 12). The beam 11 rotates along the aircraft's flight axis. The rotation mechanism ensures compactness and ease of transportation of the unmanned aerial vehicle.

[0047] A quadcopter with the "Quad+" configuration (Fig. 13) comprises a hollow body 9 made in the form of a cylindrical tube. Inside the body 9, a beam rotation mechanism with an avionics platform 12 is located. A fixed beam 10 with propeller-motor groups directed with screws upwards is fixed to the hub 1, and a rotating beam 11 with propeller-motor groups directed with screws downwards is fixed 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 rotation of the beam 11 is carried out, two symmetrically located eyes 13 are made along the trajectory of the rotation of the beam. Means for fastening and securing the rotating beam 14 in the form of screw aluminum nuts are mounted on the rotating beam. Fixed parts of the engagement group are mounted on the body 9, having a mating part for fastening the screw nuts.The upper portion of the hollow housing 9, above the beam rotation mechanism 12, houses the power unit, consisting of two batteries 15 mounted on a platform 16. The housing is closed at the top by a cover 17. The beam 11 is rotated by the rotation mechanism 12, which ensures the compactness and ease of transportation of the unmanned aerial vehicle. The front and rear electric motors are inverted so that the propellers attached to them point downward (Quad+ arrangement). This arrangement of the propeller-motor groups improves the stability of the aircraft during flight.

[0048] Procedure: During deployment, the operator positions the aircraft horizontally on the ground or other solid surface, then rotates the beam (11) around its axis in the horizontal plane, bringing it to the flight position. The operator then secures the beam (11) in place using aluminum screw nuts (14). To fold and transport the aircraft, the operator performs these steps in reverse order: loosen the nuts (14) and rotate the beam (11) in the opposite direction, then secures the beam (11) in the transport position using the nuts.

[0049] This utility model is disclosed above with reference to a specific embodiment thereof. Other embodiments of this utility model are also obvious, without changing its essence as disclosed in the above description.

[0050] 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. An unmanned aerial vehicle comprising a body, two beams with propeller-motor groups, a beam rotation mechanism, wherein the two beams and the beam rotation mechanism are installed coaxially, and the beams are located in different horizontal planes, one beam is fixed and is fixedly attached to the beam rotation mechanism, the other beam is rotary and is attached to the beam rotation mechanism with the ability to rotate the beam in a horizontal plane around its axis, characterized in that the body is hollow, and the beam rotation mechanism is located inside the hollow body, and in the wall of the hollow body at the intersection of the wall of the body with the horizontal plane in which the beam rotates, two symmetrically located eyes are made along the trajectory of the beam rotation.

2. An unmanned aerial vehicle according to paragraph 1, characterized in that the beam rotation mechanism comprises a hub, a bracket, a ball bearing and a clamp, wherein the ball bearing is located on the bracket and is rigidly attached to the bracket using a clamp, and the hub is mounted on the ball bearing with the possibility of rotation of the bracket relative to the hub.

3. An unmanned aerial vehicle according to paragraph 2, characterized in that the fixed beam is fixedly attached to the hub, and the rotating beam is fixedly attached to the bracket of the beam rotating mechanism.

4. An unmanned aerial vehicle according to paragraph 1, characterized in that the rotating beam and the body are provided with means for securing and fixing the rotating beam with the possibility of securing and fixing the rotating beam in the flight position or in the transport position.

5. An unmanned aerial vehicle according to paragraph 4, characterized in that the means for fastening and securing the rotating beam are made of an aluminum alloy.

6. An unmanned aerial vehicle according to paragraph 4, characterized in that the means for fastening and securing the rotating beam are made of thermoplastic polymers.

7. An unmanned aerial vehicle according to paragraph 4, characterized in that the fastening means are screw nuts secured to the rotating beam, and counter parts for fastening the screw nuts, made in the body.

8. An unmanned aerial vehicle according to paragraph 1, characterized in that it is a quadcopter with a “Quad+” configuration.

9. An unmanned aerial vehicle according to paragraph 1, characterized in that the propellers of the propeller-motor groups on the fixed beam are directed upward, and the propellers of the propeller-motor groups on the rotating beam are directed downward.

10. An unmanned aerial vehicle according to paragraph 1, characterized in that the power plant and avionics are located inside the body.

11. An unmanned aerial vehicle according to paragraph 1, characterized in that the body is made in the form of a cylindrical tube.

12. An unmanned aerial vehicle according to paragraph 1, characterized in that the body is made of composite materials.

13. An unmanned aerial vehicle according to paragraph 1, characterized in that a payload is located inside the body, made in the form of at least one removable module.

14. An unmanned aerial vehicle according to claim 13, characterized in that the removable module is at least a system for spraying liquid plant protection products and fertilizers, a system for scattering solid plant protection products and fertilizers, a release system, and a loudspeaker.

15. An unmanned aerial vehicle according to paragraph 1, characterized in that it contains a removable chassis, while the body is shortened.

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