A three-blade hub structure of unmanned helicopter with flapping

Abstract

The utility model relates to unmanned helicopter technical field discloses a kind of unmanned helicopter three-paddle hub structure with waving, including rotor disc assembly and rotor paddle clamp component;The rotor disc assembly includes paddle disc upper clamping plate, paddle disc lower supporting plate, hub center piece, limiting support and limiting seat.This scheme effectively overcomes the conventional unmanned aerial vehicle hub structure complex, numerous parts, weight is heavy and the like insufficient.In addition, by innovative design Y type flexible pull-twist piece, paddle clamp component can release the waving movement of paddle blade, thereby solve the problem that traditional unmanned aerial vehicle hub is too large, vibration level is too high.This improvement not only simplifies the structure of unmanned helicopter hub, but also significantly reduces the weight and the number of parts of hub, effectively reduces the stress and vibration of entire hub, greatly improves the reliability and stability of hub system.

Description

Technical Field

[0001] This utility model relates to the field of unmanned helicopter technology, specifically to a three-rotor hub structure for an unmanned helicopter with waving arms. Background Technology

[0002] As the core component of unmanned helicopters, the rotor hub is mainly responsible for converting the rotational power of the main rotor into lift. Its structural design and performance are directly related to the helicopter's flight stability, load capacity, and service life.

[0003] Currently, rotor hubs used in unmanned helicopters are mainly classified into three types: rigid, semi-rigid, and flexible. Rigid and semi-rigid rotor hubs, by simplifying or eliminating traditional flapping and oscillating hinge structures, have improved flight speed and simplified the structure to some extent. However, because the connection between the blades and the hub is rigid, the loads generated by blade flapping and oscillation during flight are entirely borne by the hub, resulting in high structural weight, high vibration levels, and limited service life. Furthermore, these hubs are expensive to manufacture and have a large number of parts, further increasing maintenance complexity and overall weight, which is detrimental to improving the overall performance and economy of unmanned helicopters.

[0004] Therefore, there is an urgent need for a rotor hub structure that is simple in structure, lightweight, low in vibration, and highly reliable, in order to solve the aforementioned problems of existing rigid and semi-rigid rotor hubs in unmanned helicopter applications. Utility Model Content

[0005] The purpose of this invention is to provide a three-rotor hub structure for an unmanned helicopter with waving arms, in order to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, this utility model provides the following technical solution:

[0007] A technical solution for a three-rotor hub structure of an unmanned helicopter with waving, including a rotor disk assembly and a rotor clip assembly;

[0008] The rotor disk assembly includes an upper disk clamping plate, a lower disk support plate, a rotor hub center piece, a limiting bracket, and a limiting seat. The upper disk clamping plate is connected to the rotor main shaft via a spline. The upper disk clamping plate and the lower disk support plate are connected by a disk-torsion plate bolt and clamp a Y-type torsion plate.

[0009] The rotor clamp assembly includes a rotor clamp, a Y-shaped tension-torsion plate, a ball bearing, and a limiting seat. The Y-shaped tension-torsion plate is connected to the rotor clamp via a tension-torsion plate-rotor clamp bolt. The rotor clamp is connected to the rotor blade via a blade mounting bolt and a blade oscillation bolt. An oscillation sleeve is provided on the outside of the blade oscillation bolt.

[0010] The paddle clamp is equipped with an observation window for observing the state of the internal tension and torsion plates;

[0011] A spring, guide pin, and guide ball head are provided between the upper clamping plate and the lower support plate of the propeller disk.

[0012] As a preferred technical solution, the limiting bracket is installed on the paddle disc clamp to limit the range of motion of the paddle clamp assembly in the swinging and oscillating directions.

[0013] As a preferred technical solution, the limiting seat is installed on the lower support plate of the propeller disk, and a limiting ring is provided on it to limit the downward swing amplitude of the propeller blade in a stationary state and prevent it from colliding with the fuselage.

[0014] As a preferred technical solution, the Y-shaped tension-torsion plate is a flexible structure that enables the blade to flap and oscillate, reducing vibration transmission.

[0015] As a preferred technical solution, the ball bearing is located inside the center component of the propeller hub to bear the load transmitted from the propeller clamp assembly and realize the pitch function.

[0016] As a preferred technical solution, the oscillation sleeve is fitted outside the blade oscillation bolt, acting as a damper for oscillation motion and absorbing oscillation energy. The blade hub center piece is provided with a blade hub counterweight block, which is used to dynamically balance the unbalanced force during the rotor rotation process. There are two observation windows, symmetrically arranged on the rear side of the blade clamp, which facilitates visual inspection of the tension and torsion plate status.

[0017] Compared with the prior art, the beneficial effects of this utility model are:

[0018] This invention relates to a three-rotor hub structure for unmanned helicopters with flapping motion. This solution effectively overcomes the shortcomings of conventional UAV rotor hub structures, such as complexity, numerous parts, and excessive weight. Furthermore, through an innovative design of a Y-shaped flexible tension-torsion plate, the rotor clamp assembly can release the flapping motion of the blades, thereby solving the problems of excessive stress and high vibration levels in traditional UAV rotor hubs. This improvement not only simplifies the structure of the unmanned helicopter rotor hub but also significantly reduces its weight and the number of parts, effectively reducing the stress and vibration of the entire hub and greatly improving the reliability and stability of the rotor hub system. Attached Figure Description

[0019] Figure 1 A three-dimensional structural diagram of a three-rotor hub structure for an unmanned helicopter with a waving arm.

[0020] Figure 2 A schematic diagram of the cross-sectional structure of a three-rotor hub structure for an unmanned helicopter with waving arms;

[0021] Figure 3 This is a schematic diagram of the three-rotor hub structure of an unmanned helicopter with a waving arm.

[0022] In the attached diagram, the following are the reference numerals: 1. Blade oscillation bolt; 2. Blade mounting bolt; 3. Torsion plate-blade clamp bolt; 4. Blade clamp; 5. Blade disk-torsion plate bolt; 6. Blade disk upper clamp plate; 7. Blade hub center component; 8. Observation window; 9. Blade hub counterweight; 10. Oscillating sleeve; 11. Y-type tension plate; 12. Ball bearing; 13. Limiting bracket; 14. Spring; 15. Guide pin; 16. Guide pin ball head; 17. Limiting seat; 18. Blade disk lower support plate; 19. Limiting ring. Detailed Implementation

[0023] The features and exemplary embodiments of various aspects of this utility model will now be described in detail. To make the objectives, technical solutions, and advantages of this utility model clearer, the following description, in conjunction with the accompanying drawings and specific embodiments, will provide a further detailed description. For those skilled in the art, this utility model can be implemented without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of this utility model by illustrating examples.

[0024] like Figure 1 , Figure 2 and Figure 3 As shown, this utility model provides a three-rotor hub structure technical solution for an unmanned helicopter with a waving arm: including a rotor disk assembly and a rotor clamp assembly. The rotor disk assembly mainly consists of an upper rotor disk clamping plate 6, a lower rotor disk support plate 18, a hub center piece 7, a limiting bracket 13, and a limiting seat 17. The upper rotor disk clamping plate 6 is connected to the rotor main shaft via a spline to ensure stable power transmission. The upper rotor disk clamping plate 6 and the lower rotor disk support plate 18 are connected by rotor disk-torsion plate bolts 5, clamping Y-shaped torsion plates 11 to form a stable structural support.

[0025] The rotor clamp assembly includes a rotor clamp 4, a Y-shaped tension / torsion plate 11, a ball bearing 12, and a limiting seat 17. The Y-shaped tension / torsion plate 11, as a flexible structure, is connected to the rotor clamp 4 via the tension / torsion plate-paddle clamp bolt 3, enabling flapping and oscillating movements of the rotor blades and effectively reducing vibration transmission. The rotor clamp 4 is connected to the rotor blades via the rotor blade mounting bolt 2 and the rotor blade oscillation bolt 1, ensuring stable installation of the rotor blades. An oscillation sleeve 10 is provided on the outer side of the rotor blade oscillation bolt 1, acting as a damper for oscillation movement and absorbing oscillation energy.

[0026] An observation window 8 is provided on the propeller clamp 4 to observe the status of the internal tension and torsion plates, facilitating the timely detection and handling of potential problems. A spring 14, a guide pin 15, and a guide ball head 16 are also provided between the upper clamping plate 6 and the lower support plate 18 of the propeller disk to further enhance the stability and reliability of the structure.

[0027] The limiting bracket 13 is installed on the propeller disk upper clamping plate 6 to limit the range of movement of the propeller clamping assembly in the flapping and oscillating directions, ensuring that the propeller blades move within a reasonable range. The limiting seat 17 is installed on the propeller disk lower support plate 18, and a limiting ring 19 is provided on it to limit the downward swing amplitude of the propeller blades in a stationary state, preventing collision with the fuselage.

[0028] The ball bearing 12 is located inside the rotor hub center component 7 to bear the load transmitted from the rotor clamp assembly and to realize the pitch function, ensuring the flexibility and stability of the rotor hub system. The rotor hub center component 7 is also equipped with a rotor hub counterweight 9 to dynamically balance the unbalanced forces during rotor rotation, further improving the performance of the rotor hub system.

[0029] There are two observation windows 8, symmetrically located on the rear side of the propeller clamp 4, which facilitates visual inspection of the tension and torsion plate status and ensures the safe operation of the propeller hub system.

[0030] The three-rotor hub structure of the unmanned helicopter with flapping blades in this embodiment utilizes an innovative Y-shaped flexible tension-torsion plate 11 to allow the rotor clamp assembly to release the flapping motion of the blades, thereby solving the problems of excessive stress and high vibration levels in traditional UAV rotor hubs. This improvement not only simplifies the structure of the unmanned helicopter rotor hub but also significantly reduces its weight and the number of parts, effectively reducing the stress and vibration of the entire rotor hub and greatly improving the reliability and stability of the rotor hub system.

[0031] The working principle and usage process of this utility model: After assembling the various components of this solution in sequence, work according to the above implementation methods according to actual needs to complete all working steps.

[0032] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

[0033] In the description of this utility model, it should be understood that the terms "coaxial", "bottom", "one end", "top", "middle", "other end", "upper", "side", "top", "inner", "front", "center", "both ends", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. They are only for the convenience of describing this utility model and 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 utility model.

[0034] In this utility model, unless otherwise explicitly specified and limited, the terms "installation", "setting", "connection", "fixing", "screw connection", etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; 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 or the interaction between two components. Unless otherwise explicitly limited, those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0035] The embodiments described above are not exhaustive, nor do they limit the invention to specific implementations. Clearly, many modifications and variations can be made based on the above description. These embodiments are selected and specifically described in this specification to better explain the principles and practical applications of the invention, enabling those skilled in the art to effectively utilize the invention and its modifications. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the invention should be included within the protection scope of the invention.

Claims

1. A three-rotor hub structure for an unmanned helicopter with waving arms, characterized in that, Includes rotor disk assembly and rotor clip assembly; The rotor disk assembly includes an upper disk clamping plate (6), a lower disk support plate (18), a hub center piece (7), a limiting bracket (13), and a limiting seat (17). The upper disk clamping plate (6) is connected to the rotor main shaft via a spline. The upper disk clamping plate (6) and the lower disk support plate (18) are connected by a disk-torsion plate bolt (5) and clamp a Y-type torsion plate (11). The rotor clamp assembly includes a rotor clamp (4), a Y-shaped tension-torsion plate (11), a ball bearing (12), and a limiting seat (17). The Y-shaped tension-torsion plate (11) is connected to the rotor clamp (4) via a tension-torsion plate-rotor clamp bolt (3). The rotor clamp (4) is connected to the rotor blade via a blade mounting bolt (2) and a blade oscillation bolt (1). An oscillation sleeve (10) is provided on the outside of the blade oscillation bolt (1). The paddle clip (4) is provided with an observation window (8) for observing the state of the internal tension and torsion plates; A spring (14), a guide pin, and a guide ball head (16) are provided between the upper clamping plate (6) of the propeller disk and the lower support plate (18) of the propeller disk.

2. The three-rotor hub structure for an unmanned helicopter with waving mechanism according to claim 1, characterized in that: The limiting bracket (13) is installed on the upper clamp plate (6) of the propeller disk to limit the range of motion of the propeller clamp assembly in the swing and oscillation directions.

3. The three-rotor hub structure for an unmanned helicopter with waving mechanism according to claim 1, characterized in that: The limiting seat (17) is installed on the propeller disk lower support plate (18), and a limiting ring (19) is provided on it to limit the downward swing amplitude of the propeller blade in a stationary state and prevent it from colliding with the fuselage.

4. The three-rotor hub structure for an unmanned helicopter with waving mechanism according to claim 1, characterized in that: The Y-shaped tension-torsion plate (11) is a flexible structure that enables the blade to flap and swing, reducing vibration transmission.

5. The three-rotor hub structure for an unmanned helicopter with waving mechanism according to claim 1, characterized in that: The ball bearing (12) is located inside the center part (7) of the propeller hub and is used to bear the load transmitted from the propeller clamp assembly and realize the pitch function.

6. The three-rotor hub structure for an unmanned helicopter with waving mechanism according to claim 1, characterized in that: The oscillation sleeve (10) is fitted outside the blade oscillation bolt (1) and acts as a damper for oscillation motion to absorb oscillation energy. The hub center piece (7) is provided with a hub counterweight (9) to dynamically balance the unbalanced force during rotor rotation. There are two observation windows (8) symmetrically arranged on the rear side of the blade clamp (4) to facilitate visual inspection of the tension and torsion plate status.

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