An unmanned aerial vehicle rotor, an assembly method of the rotor, and a rotor-type unmanned aerial vehicle

Abstract

The present invention relates to a drone rotor and a rotor-type drone. An installation groove is provided on the drone fuselage, and a groove cover is fixedly connected above the installation groove. A propeller blade is arranged above the groove cover. An internal gear ring, an external gear disc and a motor are arranged inside the installation groove. The internal gear ring is fixed to the inner bottom wall of the installation groove. The inner surface of the internal gear ring meshes with the external gear disc. The upper surface of the external gear disc is fixed with a motor. The output end of the motor is connected upward to a rotating shaft. A central hole is provided at the center position of the groove cover. The propeller blade has a downward connecting shaft. The lower end of the connecting shaft passes through the central hole. A connecting groove is provided inside the lower end of the connecting shaft. The rotating shaft is inserted into the connecting groove. Internal thread grooves with the same size are provided inside the upper part of the connecting shaft and the rotating shaft. A high-strength bolt passes through the connecting shaft and the rotating shaft from top to bottom, and the upper end is locked with a nut. The present invention preferably solves the connection problem between the drone fuselage and the rotor, not only with firm connection, but also with strong flexibility, and can preferably meet the needs of rapid disassembly, assembly and replacement of parts of the drone.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, in particular to a rotor of an unmanned aerial vehicle, an assembly method of the rotor, and a rotor-type unmanned aerial vehicle. Background Art

[0002] An unmanned aerial vehicle, abbreviated as "UAV", is an unpiloted aircraft controlled by radio remote control equipment and a self-contained program control device, or is completely or intermittently autonomously operated by an on-vehicle computer. UAVs can be divided into military and civilian according to their application fields. Militarily, UAVs are divided into reconnaissance aircraft and target drones. Civilians, in the fields of aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, observing wild animals, monitoring infectious diseases, mapping, news reporting, power inspection, disaster relief, film and television shooting, etc., these applications have greatly expanded the uses of UAVs themselves, and developed countries are also actively expanding industrial applications and developing UAV technologies.

[0003] As a type of UAV, a multi-rotor UAV is a rotor aircraft that uses the relative airflow during forward flight to blow the rotors to rotate automatically to generate lift, and its forward force is directly provided by an engine driving a propeller. Rotor UAVs have become the focus of research at home and abroad due to their advantages such as vertical takeoff and landing, free hovering, flexible control, and strong adaptability to various environments. A multi-rotor UAV is a UAV with three or more rotor axes. It drives the rotors by the rotation of the electric motors on each axis, thereby generating lift thrust. The collective pitch of the rotors is fixed, unlike that of a general helicopter which is variable. By changing the relative rotational speeds between different rotors, the magnitude of the single-axis propulsion force can be changed, thereby controlling the flight trajectory of the aircraft.

[0004] When installing the rotor mechanism of the existing rotor UAV, the motor and the blade are usually installed together by welding, and the motor is directly welded to the fuselage of the UAV. This causes inconvenience in maintenance during the maintenance process, and it is impossible to quickly disassemble or replace parts for maintenance. Due to the lack of flexibility, the welded disassembly is likely to damage the UAV or the rotor mechanism. In addition to the fixed welding structure, there are also a few rotor UAVs that use a detachable connection method, but the firmness of the connection is often unsatisfactory. The firmness and flexibility of the rotor connection cannot be achieved at the same time, which restricts the development of rotor UAVs. Summary of the Invention

[0005] In view of the above deficiencies, the present invention provides a rotor of an unmanned aerial vehicle, an assembly method of the rotor, and a rotor-type unmanned aerial vehicle, which preferably solves the connection problem between the fuselage of the unmanned aerial vehicle and the rotor. It is not only firmly connected but also highly flexible, and can preferably meet the needs of rapid disassembly, assembly, maintenance, and replacement of parts of the unmanned aerial vehicle, injecting new impetus into the development of rotor UAVs.

[0006] The technical solution of the present invention is as follows:

[0007] An unmanned aerial vehicle (UAV) rotor. The UAV includes a fuselage. An installation groove is formed in the fuselage. A groove cover is fixedly connected above the installation groove. A propeller blade is arranged above the groove cover. An internal gear ring, an external gear disc and a motor are arranged inside the installation groove. The internal gear ring is fixed to the inner bottom wall of the installation groove. The external gear disc is meshed with the inner surface of the internal gear ring. The motor is fixed to the upper surface of the external gear disc. The output end of the motor is connected upward to a rotating shaft. A central hole is formed at the center position of the groove cover. The propeller blade has a downward connecting shaft. The lower end of the connecting shaft passes through the central hole. A connecting groove adapted to the rotating shaft is formed inside the lower end of the connecting shaft. The rotating shaft is inserted into the connecting groove. Internal threaded grooves of the same size are formed inside the upper part of the connecting shaft and the rotating shaft. A high-strength bolt passes through the connecting shaft and the rotating shaft from top to bottom, and the upper end is locked with a nut.

[0008] Two positioning blocks are arranged on the upper end surface of the rotating shaft. Two corresponding positioning grooves are formed at the top of the connecting groove. The positioning blocks are inserted into the positioning grooves.

[0009] Both the positioning blocks and the positioning grooves are rectangular parallelepiped-shaped.

[0010] An installation block is fixed to the lower end surface of the groove cover. A spring is connected to the lower end of the installation block. A pressing block is connected to the lower end of the spring. When the groove cover is fixed above the installation groove, the spring is in a compressed state.

[0011] The connection method between the groove cover and the installation groove is as follows: Four threaded grooves are formed around the installation groove in a circumferential manner. Threaded holes are formed at the corresponding positions on the edge of the groove cover. The threaded holes and the threaded grooves are connected by screws.

[0012] A heat-conducting silica gel is coated on the surface of the motor.

[0013] A rotor-type unmanned aerial vehicle includes a fuselage and a UAV rotor.

[0014] The surfaces of the fuselage and the propeller blade are galvanized.

[0015] An assembly method for a UAV rotor includes the following steps:

[0016] S1: Mount the external gear disc on the inner surface of the gear of the internal gear ring;

[0017] S2: Place the groove cover above the installation groove, press downward to compress the spring, align the threaded grooves with the threaded holes, and tighten the screws;

[0018] S3: Insert the connecting shaft downward into the central hole of the groove cover, insert the rotating shaft into the connecting groove, and insert the positioning blocks into the positioning grooves;

[0019] S4: Insert the high-strength bolt into the internal thread grooves of the connecting shaft and the rotating shaft from top to bottom, and lock the upper end with a nut.

[0020] On the fuselage of the unmanned aerial vehicle (UAV) of the present invention, there are an installation groove and a groove cover. Inside the installation groove, there is a motor and a rotating shaft. Above the groove cover, there are a propeller and a connecting shaft. The rotating shaft and the connecting shaft pass through the central hole provided in the groove cover, and are connected and fixed by a high-strength bolt inserted from top to bottom, with firm installation and high connection strength. When in use, the motor drives the rotating shaft to rotate, and drives the connecting shaft and the propeller to rotate, realizing the vertical takeoff and landing and free hovering of the rotary-wing UAV. Inside the installation groove, the motor meshes with the internal gear ring and the external gear disk, achieving fixation in the horizontal direction, so that the motor will not shake left and right during the rotation process, improving the stability of the rotation process of the motor and the rotor. Between the installation groove and the groove cover, there are fastening blocks, springs and fixing blocks. The spring in the compressed state presses the external gear disk where the motor is located downward, achieving fixation of the motor in the vertical direction, so that the motor will not bounce up and down during the rotation process, further improving the stability of the rotation process of the motor and the rotor. Description of the Drawings

[0021] Figure 1 It is an exploded view of the rotor of the UAV of the present invention;

[0022] Figure 2 It is an assembled state diagram of the rotor of the UAV of the present invention;

[0023] Figure 3 It is a three-dimensional view of the external gear disk and the motor of the present invention;

[0024] Figure 4 It is an assembled state diagram of the rotating shaft and the connecting shaft of the present invention;

[0025] Figure 5 It is an exploded view of the groove cover, the installation block and the spring of the present invention;

[0026] Figure 6 It is a top view of the meshing state of the internal gear ring and the external gear disk of the present invention. Detailed Embodiments

[0027] The concept, specific structure and technical effects of the present invention will be further described below in conjunction with the drawings to fully understand the purpose, features and effects of the present invention.

[0028] Reference Figures 1 - 6, A drone rotor of the present invention, the drone includes a fuselage 100, an installation groove 11 is provided on the fuselage 100, a groove cover 12 is fixedly connected above the installation groove 11, a blade 13 is arranged above the groove cover 12, and an internal gear ring 14, an external gear disk 15 and a motor 16 are arranged inside the installation groove 11. The internal gear ring 14 is fixed to the inner bottom wall of the installation groove 11, the inner surface of the internal gear ring 14 meshes with the external gear disk 15, the upper surface of the external gear disk 15 is fixed with a motor 16, and the output end of the motor 16 is connected upward to a rotating shaft 161. Through the meshing between the internal gear ring 14 and the external gear disk 15, the motor 16 is fixed inside the installation groove 11, avoiding the horizontal shaking of the motor 16 during rotation, ensuring the fixation of the motor 16 in the horizontal direction, and improving the stability of the rotation process of the motor 15.

[0029] A central hole 121 is provided at the center position of the groove cover 12. The blade 13 has a downward connecting shaft 17. The lower end of the connecting shaft 17 passes through the central hole 121. A connecting groove 171 adapted to the rotating shaft 161 is provided inside the lower end of the connecting shaft 17. The rotating shaft 161 is inserted into the connecting groove 171. Internal thread grooves 18 of the same size are provided inside the upper part of the connecting shaft 17 and the rotating shaft 161. A high-strength bolt 19 passes through the connecting shaft 17 and the rotating shaft 161 from top to bottom, and the upper end is locked with a nut 20. The high-strength bolt 19 is made of alloy steel, can bear a large load, and improves the integrity and stiffness of the connection. The high-strength bolt 19 realizes a firm connection between the connecting shaft 17 and the rotating shaft 161. Driven by the motor 16, the rotating shaft 161, the connecting shaft 17 and the blade 13 rotate synchronously, realizing the vertical takeoff and landing and free hovering of the rotor-type drone.

[0030] In order to further strengthen the positioning between the rotating shaft 161 and the connecting shaft 17, two positioning blocks 1611 are provided on the upper end surface of the rotating shaft 161, and two corresponding positioning grooves 1711 are provided at the corresponding position of the groove top of the connecting groove 171. When the rotating shaft 161 is inserted into the connecting groove 171, the positioning blocks 1611 are inserted into the positioning grooves 1711. The positioning blocks 1611 and the positioning grooves 1711 fix the connection angle between the rotating shaft 161 and the connecting shaft 17, avoiding the relative slip and even connection failure of the two due to the decrease in shear resistance after long-term use of the high-strength bolt 19. Preferably, both the positioning blocks 1611 and the positioning grooves 1711 are rectangular parallelepipeds.

[0031] Further, the connection mode between the slot cover 12 and the installation slot 11 is as follows: Four threaded slots 111 are circumferentially formed around the installation slot 11, threaded holes 125 are correspondingly formed at the edges of the slot cover 12, and the threaded holes 125 and the threaded slots 111 are connected by screws 126. An installation block 122 is fixed to the lower end surface of the slot cover 12, a spring 123 is connected to the lower end of the installation block 122, and a pressing block 124 is connected to the lower end of the spring 123. When the slot cover 12 is fixed above the installation slot 11, the spring 123 is in a compressed state. The compressed spring 123 causes the pressing block 124 to press downward against the upper surface of the external gear disk 15 where the motor 16 is located, fixing the motor 16 in the vertical direction and preventing the motor 16 from bouncing up and down during rotation, further improving the stability of the motor 16 during rotation.

[0032] The present invention also protects a rotary-wing unmanned aerial vehicle. The rotary wing of the unmanned aerial vehicle has the structure described above. A heat-conducting silica gel is coated on the surface of the motor 16, which has good heat-conducting performance and is beneficial to the heat dissipation of the motor, keeping the motor 16 in a good working state. The surfaces of the fuselage 100 and the blade 13 are galvanized to improve the surface antioxidant performance and prevent rusting.

[0033] The assembly method of the rotary wing of the unmanned aerial vehicle of the present invention is as follows:

[0034] S1: Snap the external gear disk 15 onto the inner surface of the gear of the inner gear ring 14;

[0035] S2: Place the slot cover 12 above the installation slot 11, press downward to compress the spring 123, align the threaded slot 111 with the threaded hole 125, and tighten the screw 126;

[0036] S3: Insert the connecting shaft 17 downward into the central hole 121 of the slot cover 12, insert the rotating shaft 161 into the connecting slot 171, and insert the positioning block 1611 into the positioning slot 1711;

[0037] S4: Insert the high-strength bolt 19 from top to bottom into the internal threaded slot 18 of the connecting shaft 17 and the rotating shaft 161, and lock the upper end with a nut 20.

[0038] The rotary wing of the unmanned aerial vehicle and the rotary-wing unmanned aerial vehicle of the present invention preferably solve the connection problem between the fuselage and the rotary wing of the unmanned aerial vehicle. They are not only firmly connected but also highly flexible, and can preferably meet the needs of the unmanned aerial vehicle for quick disassembly, assembly, maintenance, replacement of parts, etc., injecting new impetus into the development of the rotary-wing unmanned aerial vehicle.

[0039] The above-disclosed are only the embodiments of the present invention. However, the present invention is not limited thereto, and any changes that can be conceived by those skilled in the art should fall within the protection scope of the present invention.

Claims

1. A drone rotor, the drone comprising a fuselage (100), characterized in that, An installation groove (11) is formed in the fuselage (100). A groove cover (12) is fixedly connected above the installation groove (11). A propeller blade (13) is arranged above the groove cover (12). An internal gear ring (14), an external gear disc (15) and a motor (16) are arranged inside the installation groove (11). The internal gear ring (14) is fixed to the inner bottom wall of the installation groove (11). The inner surface of the internal gear ring (14) meshes with the external gear disc (15). The upper surface of the external gear disc (15) is fixed with the motor (16). The output end of the motor (16) is connected upward to a rotating shaft (161). A central hole (121) is formed at the central position of the groove cover (12). The propeller blade (13) has a downward connecting shaft (17). The lower end of the connecting shaft (17) passes through the central hole (121). A connecting groove (171) adapted to the rotating shaft (161) is formed inside the lower end of the connecting shaft (17). The rotating shaft (161) is inserted into the connecting groove (171). Internal thread grooves (18) of the same size are formed inside the upper part of the connecting shaft (17) and the rotating shaft (161). A high-strength bolt (19) passes through the connecting shaft (17) and the rotating shaft (161) from top to bottom, and the upper end is locked with a nut (20). Two positioning blocks (1611) are arranged on the upper end surface of the rotating shaft (161). Two corresponding positioning grooves (1711) are formed at the top of the connecting groove (171). The positioning blocks (1611) are inserted into the positioning grooves (1711). An installation block (122) is fixed to the lower end surface of the groove cover (12). The lower end of the installation block (122) is connected to a spring (123). The lower end of the spring (123) is connected to a pressing block (124). When the groove cover (12) is fixed above the installation groove (11), the spring (123) is in a compressed state.

2. The drone rotor according to claim 1, wherein, Both the positioning blocks (1611) and the positioning grooves (1711) are rectangular parallelepiped-shaped.

3. The drone rotor according to claim 1, characterized in that, The connection manner between the groove cover (12) and the installation groove (11) is as follows: Four threaded grooves (111) are formed around the installation groove (11). Threaded holes (125) are formed at the corresponding positions on the edge of the groove cover (12). The threaded holes (125) and the threaded grooves (111) are connected by screws (126).

4. The drone rotor according to claim 1, characterized in that, The surface of the motor (16) is coated with heat-conducting silica gel.

5. A rotor-type unmanned aerial vehicle, characterized in that, It includes a fuselage (100) and a drone rotor as described in any one of claims 1-4.

6. The rotary-wing unmanned aerial vehicle according to claim 5, characterized in that, The surfaces of the fuselage (100) and the propeller blade (13) are galvanized.

7. A method for assembling a drone rotor, the method being applied to the drone rotor as described in claim 1, characterized in that: The connection manner between the groove cover (12) and the installation groove (11) is as follows: Four threaded grooves (111) are formed around the installation groove (11). Threaded holes (125) are formed at the corresponding positions on the edge of the groove cover (12). The threaded holes (125) and the threaded grooves (111) are connected by screws (126); The method includes the following steps: S1: Clamp the external gear disc (15) on the inner surface of the gear of the internal gear ring (14); S2: Place the groove cover (12) above the installation groove (11), press it down to compress the spring (123), align the threaded groove (111) with the threaded hole (125), and tighten the screw (126). S3: Insert the connecting shaft (17) downward into the central hole (121) of the groove cover (12), insert the rotating shaft (161) into the connecting groove (171), and insert the positioning block (1611) into the positioning groove (1711). S4: Insert the high-strength bolt (19) downward into the internal threaded groove (18) of the connecting shaft (17) and the rotating shaft (161), and lock the upper end with a nut (20).

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