A drone tilting mechanism

Abstract

This application discloses a tilting mechanism for a drone, belonging to the field of drones. One end of a power-end connecting component is connected to the drone's power system, and the other end is rotatably connected to a body connecting component. The end of the body connecting component away from the power-end connecting component has multiple positioning pin holes. The body connecting component is detachably connected to the drone's power arm through these positioning pin holes, and the installation angle of the tilting mechanism can be changed by selecting different positioning pin holes to connect with the drone's power arm. The power-end connecting component includes a first connecting member, a first motor support, a second connecting member, and a second motor support, all detachably connected in sequence. The body connecting component includes a first mounting base, a first connecting seat, a second mounting base, and a second connecting seat, all detachably connected in sequence. This application achieves modular assembly of the tilting mechanism, reducing manufacturing costs and improving the versatility of parts and production efficiency.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to a UAV tilting mechanism. Background Technology

[0002] The tilt mechanism is a key component in tiltrotor aircraft and other vertical takeoff and landing (VTOL) aircraft. Its main function is to enable the power system to switch angles between vertical takeoff / landing and horizontal cruise states. The structural design and manufacturing cost of the tilt mechanism directly affect the overall performance and economy of the aircraft.

[0003] Currently, most existing tilt mechanisms adopt an integrated design approach, meaning that a complete tilt mechanism is designed and manufactured separately for the specific installation angle requirements of a particular aircraft model. This approach has the following drawbacks: the tilt mechanism is usually designed and manufactured as a single integral component, resulting in complex parts and high requirements for processing equipment and processes, leading to high manufacturing costs for a single tilt mechanism; when an aircraft requires multiple tilt mechanisms with different installation angles, separate molds and manufacturing are required, making it difficult to achieve parts standardization and mass production. Utility Model Content

[0004] This application provides a drone tilting mechanism, which solves the problems mentioned in the background art.

[0005] This application provides a tilting mechanism for a drone, including a power end connection assembly and a body connection assembly. One end of the power end connection assembly is connected to the power system of the drone, and the other end is rotatably connected to the body connection assembly. The end of the body connection assembly away from the power end connection assembly has multiple positioning pin holes. The body connection assembly is detachably connected to the drone's power arm through these positioning pin holes, and the installation angle of the tilting mechanism can be changed by selecting different positioning pin holes to connect to the drone's power arm. The power end connection assembly includes a first connector, a first motor support, a second connector, and a second motor support, all detachably connected in sequence. The body connection assembly includes a first mounting base, a first connecting seat, a second mounting base, and a second connecting seat, all detachably connected in sequence.

[0006] In one possible implementation, the UAV tilting mechanism further includes a limiting assembly and a linkage assembly; the limiting assembly includes a rocker arm, a brake lever, a first limiting block, and a second limiting block; a servo mounting base is provided on the body connecting assembly for mounting a servo; the rocker arm is mounted on the output end of the servo, and the brake lever is disposed on the rocker arm; one end of the linkage assembly is hinged to the rocker arm, and the other end is hinged to the power end connecting assembly; the first limiting block and the second limiting block are spaced apart circumferentially along the servo mounting base, and when the rocker arm rotates to its limit position, the brake lever abuts against the first limiting block or the second limiting block to achieve mechanical limiting.

[0007] In one possible implementation, the power end connection assembly is rotatably connected to the body connection assembly via a rotating shaft; the end of the connecting rod assembly away from the rocker arm is hinged to a connector, and the connector is fixedly connected to the rotating shaft.

[0008] In one possible implementation, the UAV tilting mechanism further includes a force sensing component; the force sensing component is integrated on the linkage assembly and is used to monitor the axial force borne by the linkage assembly in real time.

[0009] In one possible implementation, the UAV tilting mechanism further includes an attitude sensing component; the attitude sensing component is mounted on the end of the rotating shaft and is used to monitor the vibration amplitude and rotation angle of the power end connection component in real time.

[0010] In one possible implementation, the drone tilting mechanism further includes a shock-absorbing pad; the shock-absorbing pad is disposed between the power end connection assembly and the power system end of the drone, for reducing vibration transmitted to the power end connection assembly.

[0011] One or more technical solutions provided in the embodiments of this application have at least the following technical effects: The UAV tilting mechanism provided in this application embodiment achieves modular disassembly and assembly by setting the power end connection component as a first connector, a first motor support, a second connector, and a second motor support that are detachably connected in sequence, and setting the body connection component as a first mounting base, a first connecting seat, a second mounting base, and a second connecting seat that are detachably connected in sequence. This reduces the complexity and processing difficulty of individual parts, thereby effectively reducing manufacturing costs and facilitating mass production. At the same time, by setting multiple positioning pin holes on the body connection component, the body connection component can select different positioning pin holes to connect with the UAV body power arm, thereby adapting to different installation angle requirements with a standardized tilting mechanism. This eliminates the need for separate mold manufacturing for each angle, improving the versatility of parts and production efficiency. Attached Figure Description

[0012] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments of this application will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0013] Figure 1 This is a schematic diagram of the structure of the UAV tilting mechanism provided in the embodiments of this application; Figure 2 This is a schematic diagram of the structure of the limiting component provided in the embodiments of this application; Figure 3 This is a schematic diagram of the structure of the positioning pin hole provided in an embodiment of this application; Figure 4 This is a schematic diagram of the structure of the body connection assembly provided in an embodiment of this application.

[0014] Icons: 1-Power end connection assembly; 11-First connector; 12-First motor support; 13-Second connector; 14-Second motor support; 2-Body connection assembly; 21-Positioning pin hole; 22-First mounting base; 23-First connector; 24-Second mounting base; 25-Second connector; 3-Power system end of UAV; 4-Connector; 5-Limiting assembly; 51-Rocker arm; 52-Brake lever; 53-First limit block; 54-Second limit block; 6-Linkage assembly; 7-Servo mounting base; 8-Shaft; 9-Force sensing assembly; 10-Attitude sensing assembly; 101-Shock absorber; 102-UAV body power arm. Detailed Implementation

[0015] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0016] In the description of the embodiments of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the embodiments of this application and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application according to the specific circumstances.

[0017] like Figures 1 to 4 As shown, this application embodiment provides a drone tilting mechanism. The drone tilting mechanism includes a power end connection assembly 1 and a body connection assembly 2. One end of the power end connection assembly 1 is connected to the drone's power system end 3, and the other end is rotatably connected to the body connection assembly 2. The drone's power system end 3 includes components such as a power motor and propellers that generate lift or thrust. The end of the body connection assembly 2 away from the power end connection assembly 1 is provided with multiple positioning pin holes 21. The body connection assembly 2 is detachably connected to the drone's power arm 102 through the positioning pin holes 21. The drone's power arm 102 is mainly composed of a power arm frame of the body structure and is used for detachable connection to the tilting mechanism. The body connection assembly 2 can change the installation angle of the tilting mechanism by selecting different positioning pin holes 21 to connect with the drone's power arm 102. The power end connection assembly 1 includes a first connector 11, a first motor support 12, a second connector 13, and a second motor support 14, which are detachably connected in sequence. The body connection assembly 2 includes a first mounting base 22, a first connecting seat 23, a second mounting base 24, and a second connecting seat 25 that are detachably connected in sequence.

[0018] Specifically, the first connector 11, the first motor support 12, the second connector 13, and the second motor support 14 are connected in sequence to form a first frame for connecting the power system end 3 of the UAV; the first mounting base 22, the first connecting seat 23, the second mounting base 24, and the second connecting seat 25 are connected in sequence to form a second frame for connecting the power arm 102 of the UAV body.

[0019] Furthermore, multiple positioning pin holes 21 are respectively disposed on the first mounting base 22 and the second mounting base 24, and are symmetrically arranged circumferentially. By selecting positioning pin holes 21 at different circumferential positions to cooperate with the UAV body power arm 102, multi-level adjustment of the tilting mechanism installation angle can be achieved. The multiple positioning pin holes 21 can be distributed in an arc shape or a circular array on the first mounting base 22 and the second mounting base 24, respectively.

[0020] It should be noted that the UAV tilting mechanism provided in this application embodiment, by setting the power end connecting component 1 as a first connecting piece 11, a first motor support 12, a second connecting piece 13, and a second motor support 14 that are detachably connected in sequence, and setting the body connecting component 2 as a first mounting base 22, a first connecting seat 23, a second mounting base 24, and a second connecting seat 25 that are detachably connected in sequence, realizes the modular disassembly and assembly of the tilting mechanism, reduces the complexity and processing difficulty of individual parts, thereby effectively reducing manufacturing costs and facilitating mass production; at the same time, by setting multiple positioning pin holes 21 on the body connecting component 2, the body connecting component 2 can be connected to the UAV body power arm 102 by selecting different positioning pin holes 21, thereby adapting to different installation angle requirements with a standardized tilting mechanism, without the need for separate mold manufacturing for each angle, improving the versatility of parts and production efficiency.

[0021] In this embodiment, the UAV tilting mechanism further includes a limiting component 5 and a connecting rod assembly 6. The limiting component 5 includes a rocker arm 51, a brake rod 52, a first limiting block 53, and a second limiting block 54. A servo mounting base 7 is provided on the body connecting assembly 2 for mounting the servo. The rocker arm 51 is mounted on the output end of the servo, and the brake rod 52 is mounted on the rocker arm 51. One end of the connecting rod assembly 6 is hinged to the rocker arm 51, and the other end is hinged to the power end connecting assembly 1. The first limiting block 53 and the second limiting block 54 are spaced apart circumferentially along the servo mounting base 7. When the rocker arm 51 rotates to its limit position, the brake rod 52 abuts against the first limiting block 53 or the second limiting block 54 to achieve mechanical limiting, effectively preventing the servo from overtravel and improving the safety and reliability of the tilting mechanism.

[0022] In the embodiments of this application, such as Figure 2 As shown, the end of the linkage assembly 6 away from the rocker arm 51 is hinged to the connector 4. The connector 4 is fixedly connected to the rotating shaft 8, so that the servo motor can directly drive the rotating shaft 8 to rotate through the rocker arm 51 and the linkage assembly 6, thereby driving the power end connecting assembly 1 to tilt around the axis of the rotating shaft 8. The transmission path is short and the structure is compact, which improves the response speed and transmission efficiency of the tilting action.

[0023] In this embodiment, the UAV tilting mechanism further includes a force sensing component 9. The force sensing component 9 is integrated onto the linkage assembly 6 and is used to monitor the axial force borne by the linkage assembly 6 in real time, acquire force value data under normal and motion conditions, and accurately assess the health status of the tilting mechanism by comparing and analyzing the accumulated data, promptly detecting abnormalities and ensuring the flight safety of the UAV.

[0024] In this embodiment of the application, the UAV tilting mechanism also includes an attitude sensing component 10, which is installed at the end of the rotating shaft 8 and is used to monitor the vibration amplitude and rotation angle of the power end connection component 1 in real time. The measured rotation angle is compared with the drive angle of the servo motor to determine whether there is a transmission error or abnormal vibration in the tilting mechanism, and to provide data support for the health monitoring and fault warning of the tilting mechanism.

[0025] In this embodiment, the UAV tilting mechanism further includes a shock-absorbing pad 101. The shock-absorbing pad 101 is disposed between the power-end connection component 1 and the power system end 3 of the UAV, and can effectively absorb and reduce the transmission of high-frequency vibrations generated at the power system end to the power-end connection component 1, reduce the impact of vibration on various components of the tilting mechanism, extend the service life of the tilting mechanism, and improve its operational stability and reliability.

[0026] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, please refer to each other. Each embodiment focuses on describing the differences from other embodiments.

[0027] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of this application.

Claims

1. A tilting mechanism for unmanned aerial vehicles (UAVs), characterized in that, It includes a power end connection assembly (1) and a body connection assembly (2); One end of the power end connection component (1) is used to connect to the power system end (3) of the UAV, and the other end is rotatably connected to the body connection component (2). The body connection assembly (2) has a plurality of positioning pin holes (21) at one end away from the power end connection assembly (1). The body connection assembly (2) is detachably connected to the drone body power arm (102) through the positioning pin holes (21). The body connection assembly (2) can change the installation angle of the tilting mechanism by selecting different positioning pin holes (21) to connect to the drone body power arm (102). The power end connection assembly (1) includes a first connector (11), a first motor support (12), a second connector (13), and a second motor support (14) that are detachably connected in sequence. The body connection assembly (2) includes a first mounting base (22), a first connecting seat (23), a second mounting base (24), and a second connecting seat (25) that are detachably connected in sequence.

2. The UAV tilting mechanism according to claim 1, characterized in that, It also includes a limit assembly (5) and a linkage assembly (6); The limiting component (5) includes a rocker arm (51), a brake lever (52), a first limiting block (53), and a second limiting block (54); The body connection assembly (2) is provided with a servo motor mounting base (7) for mounting a servo motor; The rocker arm (51) is mounted on the output end of the servo motor, and the brake lever (52) is mounted on the rocker arm (51); One end of the connecting rod assembly (6) is hinged to the rocker arm (51), and the other end is hinged to the power end connection assembly (1); The first limiting block (53) and the second limiting block (54) are spaced apart along the circumference of the servo mounting base (7). When the rocker arm (51) rotates to the limit position, the brake rod (52) abuts against the first limiting block (53) or the second limiting block (54) to achieve mechanical limiting.

3. The UAV tilting mechanism according to claim 2, characterized in that, The power end connection assembly (1) is rotatably connected to the body connection assembly (2) via a rotating shaft (8); The end of the connecting rod assembly (6) away from the rocker arm (51) is hinged to the connector (4), and the connector (4) is fixedly connected to the rotating shaft (8).

4. The UAV tilting mechanism according to claim 3, characterized in that, It also includes a force sensing component (9); The force sensing component (9) is integrated on the connecting rod assembly (6) and is used to monitor the axial force borne by the connecting rod assembly (6) in real time.

5. The UAV tilting mechanism according to claim 3, characterized in that, It also includes an attitude sensing component (10); The attitude sensing component (10) is installed at the end of the rotating shaft (8) and is used to monitor the vibration amplitude and rotation angle of the power end connection component (1) in real time.

6. The UAV tilting mechanism according to claim 1, characterized in that, It also includes a shock-absorbing pad (101); The shock-absorbing pad (101) is disposed between the power end connection assembly (1) and the power system end (3) of the UAV to reduce the vibration transmitted to the power end connection assembly (1).

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