Bearingless rotor hub and flexible beam propeller
By using a bearingless rotor hub and a flexible beam propeller, the problem of uneven blade lift was solved, resulting in more efficient load transfer and more stable flight performance, thus improving the speed and endurance of the aircraft.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-26
- Publication Date
- 2026-03-06
AI Technical Summary
The existing fixed-pitch propeller clamp mechanism causes uneven lift on the blades, resulting in vibration and failure to release bending moment momentum, which affects the flight stability and efficiency of the aircraft.
By employing a bearingless rotor hub and a flexible beam propeller, the blade flapping, oscillation, and pitch-variable motions are achieved through the bearingless rotor system and flexible beam propeller structure. The blade shape is optimized to uniformly transmit the load and reduce drag.
It improves the aircraft's flight speed and stability, increases its range and time, reduces overall drag, and enhances flight performance.
Smart Images
Figure CN223972724U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of propeller technology, specifically to a bearingless rotor hub and flexible beam propeller. Background Technology
[0002] With the continuous maturation of flight control technology and motor technology, aircraft are being used more and more widely in the civilian field. Currently, these aircraft use a certain mechanical connection structure to mount the propeller on the drive motor. The connection structure plays a role in fixing the propeller, transmitting lift, and transmitting torque.
[0003] In contrast, some devices on the market typically use conventional fixed-pitch multi-rotor rotor clamps to restrict the free movement of the rotor blades in the vertical and horizontal directions relative to the rotor plane. During the flight of the aircraft, the air convection velocity experienced by the rotor blades will be different at different positions, and the lift experienced by the rotor blades at different positions will also be different. The relative airflow velocity of the forward rotor blades in the rotor plane is greater than that of the backward rotor blades, and the lift generated is also greater for the forward rotor blades than for the backward rotor blades.
[0004] However, in actual use, the fixed pitch propeller clamp mechanism of the above-mentioned equipment has uneven lift on both sides of the aircraft's clamp, and the clamp restricts the free movement of the blade in the up, down and forward and backward directions relative to the blade plane, which causes the bending moment momentum generated during the blade swing to be unable to be released and thus causes vibration. In view of this, we propose a bearingless rotor hub and flexible beam propeller. Utility Model Content
[0005] The purpose of this invention is to provide a bearingless rotor hub and a flexible beam propeller to solve the problems mentioned in the background art.
[0006] To achieve the above objectives, this utility model provides the following technical solution: a bearingless rotor hub, comprising a hub central assembly, a hub upper pressure plate disposed on the upper surface of the hub central assembly, a bolt disposed on the upper surface of the hub upper pressure plate, a nut being threaded onto the outer surface of the bolt, and a positioning assembly disposed on the inner wall of the hub central assembly, the positioning assembly comprising:
[0007] A positioning ring is fixedly connected to the bottom of the inner wall of the central component of the propeller hub. A reinforcing member is fixedly connected to the upper surface of the upper pressure plate of the propeller hub, and a positioning rod is fixedly connected to the bottom of the upper pressure plate of the propeller hub.
[0008] Preferably, the position of the positioning rod corresponds to the position of the positioning ring, and the size of the positioning rod is adapted to the size of the positioning ring, so that the positioning rod can be well inserted into the interior of the positioning ring.
[0009] Preferably, the size of the pressure plate on the propeller hub is adapted to the size of the central assembly of the propeller hub, so that the pressure plate on the propeller hub, together with the central assembly of the propeller hub, can effectively limit the propeller assembly.
[0010] Preferably, the base of the central component of the propeller hub is a flange structure with pre-drilled bolt holes, and the reinforcing member is arranged in an X shape, which makes the pressure plate on the propeller hub stronger.
[0011] A flexible beam propeller includes a propeller assembly, the propeller assembly including a propeller intermediate mounting section, a propeller metal bushing fixedly connected to the center of the upper surface of the propeller intermediate mounting section, a propeller flexible beam flapping deformation section fixedly connected to the side of the propeller intermediate mounting section, and a propeller airfoil section fixedly connected to the side of the propeller flexible beam flapping deformation section.
[0012] Preferably, the size of the intermediate mounting section of the propeller is adapted to the size of the central assembly of the propeller hub, and the center of the intermediate mounting section of the propeller corresponds to the position of the positioning ring.
[0013] Preferably, the propeller metal bushing is located at the center of the propeller intermediate mounting section, and the number of the propeller flexible beam flapping deformation sections is two, with the two propeller flexible beam flapping deformation sections symmetrically arranged with respect to the center of the propeller intermediate mounting section.
[0014] Compared with the prior art, this utility model provides a bearingless rotor hub and a flexible beam propeller, which has the following advantages:
[0015] 1. The bearingless rotor hub and flexible beam propeller are designed to ensure more uniform lift on both sides of the rotor hub. The aircraft adopts a bearingless rotor system, which has high load transfer efficiency. The hub structure is simple, lightweight, and has low manufacturing cost. The bearingless rotor hub also has low drag. Compared with integrated blades and split blades, no additional fairing is required, resulting in high flight efficiency and an aesthetically pleasing overall appearance. Compared with the fixed-pitch propeller clamp mechanism in the existing technology, the bearingless rotor hub and flexible beam blade configuration result in more uniform lift on both sides of the aircraft.
[0016] 2. This bearingless rotor hub and flexible beam propeller, in order to improve the speed and stability of the aircraft, uses a flexible beam blade structure to replace flapping, flaring, and pitch-changing hinges. The blade flapping, flaring, and pitch-changing motion are achieved through its own deformation. The shape is optimized according to different airfoils, resulting in low drag and high efficiency. It can effectively improve the flight speed of the aircraft, increase the range and time, and improve the flight performance of the aircraft. The flexible beam propeller blades can reduce the drag generated by the engine and improve the speed and stability of the aircraft. Attached Figure Description
[0017] Figure 1 This is a front view structural diagram of the present invention;
[0018] Figure 2 This is a top view of the structure of this utility model;
[0019] Figure 3 This is a top view schematic diagram of the propeller wing structure of this utility model;
[0020] Figure 4 This is a three-dimensional left-side view of the rotor hub structure of this utility model;
[0021] Figure 5 This is a schematic diagram of the exploded structure of the rotor hub of this utility model;
[0022] Figure 6 This is a schematic diagram of the structure of the propeller hub central component assembly of this utility model;
[0023] Figure 7 This is a schematic diagram of the pressure plate structure on the propeller hub of this utility model.
[0024] In the diagram: 1. Central hub assembly; 2. Upper hub pressure plate; 3. Bolt; 4. Nut; 7. Positioning assembly; 701. Positioning ring; 702. Reinforcing member; 703. Positioning rod; 8. Propeller assembly; 801. Intermediate propeller mounting section; 802. Propeller metal bushing; 803. Flexible beam flapping deformation section of the propeller; 804. Airfoil section of the propeller. Detailed Implementation
[0025] like Figures 1-7 As shown, this utility model provides a technical solution: a bearingless rotor hub, including a hub central assembly 1. The base of the hub central assembly 1 is a flange structure with reserved mounting bolt holes. A hub upper pressure plate 2 is provided on the upper surface of the hub central assembly 1. The size of the hub upper pressure plate 2 is adapted to the size of the hub central assembly 1, so that the hub upper pressure plate 2 can work well with the hub central assembly 1 to limit the propeller assembly 8. A bolt 3 is provided on the upper surface of the hub upper pressure plate 2. A nut 4 is threaded on the outer surface of the bolt 3. A positioning component 7 is provided on the inner wall of the hub central assembly 1.
[0026] In an embodiment of this utility model, the positioning component 7 includes a positioning ring 701, which is fixedly connected to the bottom of the inner wall of the central component 1 of the propeller hub. A reinforcing member 702 is fixedly connected to the upper surface of the upper pressure plate 2 of the propeller hub. The reinforcing member 702 is arranged in an X shape, which makes the upper pressure plate 2 of the propeller hub stronger. A positioning rod 703 is fixedly connected to the bottom of the upper pressure plate 2 of the propeller hub. The position of the positioning rod 703 corresponds to the position of the positioning ring 701. The size of the positioning rod 703 is adapted to the size of the positioning ring 701, which allows the positioning rod 703 to enter the interior of the positioning ring 701 well.
[0027] A flexible beam propeller includes a propeller assembly 8, which includes a central mounting section 801. The size of the central mounting section 801 is adapted to the size of the central hub assembly 1. The center of the central mounting section 801 corresponds to the position of a positioning ring 701. A propeller metal bushing 802 is fixedly connected to the center of the upper surface of the central mounting section 801. The position of the propeller metal bushing 802 is at the center of the central mounting section 801. Two flexible beam flapping deformation sections 803 are fixedly connected to the side of the central mounting section 801. The flapping deformation section 803 is symmetrically arranged at the center of the propeller intermediate mounting section 801. The propeller flexible beam flapping deformation section 803 is fixedly connected to the side of the propeller airfoil section 804. In this way, the propeller flexible beam flapping deformation section 803, which is fixedly connected to the side of the propeller intermediate mounting section 801, can achieve flapping, oscillation and pitch change motion of the propeller blades through its own deformation during the rotation of the propeller assembly 8. The shape can be optimized according to different airfoils, which can effectively improve the flight speed of the aircraft, increase the range and time, and improve the flight performance of the aircraft. The flexible beam propeller blades can reduce the drag generated by the engine and improve the speed and stability of the aircraft.
[0028] In this invention, during use, the propeller intermediate mounting section 801 is placed inside the propeller hub central assembly 1, allowing the propeller intermediate mounting section 801 to fit snugly inside the propeller hub central assembly 1. The propeller hub upper pressure plate 2 is then installed on the outer surface of the propeller intermediate mounting section 801, merging the propeller hub upper pressure plate 2 with the propeller hub central assembly 1. This allows the positioning rod 703 to pass through the propeller intermediate mounting section 801 and enter the propeller hub central assembly 1. Then, the bolt 3 passes through the reinforcing member 702, the propeller hub upper pressure plate 2, and the propeller hub central assembly 1, and is threadedly connected to the nut 4. This allows the propeller assembly 8 to be well-limited. Furthermore, the aircraft adopts a bearingless rotor system, which has high load transmission efficiency due to the bearingless rotor hub and flexible beam propeller. The hub structure is simple, lightweight, and has low manufacturing cost. Moreover, the bearingless rotor hub has low drag, making the lift on both sides of the bearingless rotor hub of the aircraft more uniform.
[0029] Furthermore, the flexible beam flapping and deformation section 803 of the propeller, which is fixedly connected to the side of the middle section 801 of the propeller, can achieve flapping, oscillation and pitch change of the blades through its own deformation during the rotation of the propeller assembly 8. The shape is optimized according to different airfoils, and can effectively improve the flight speed of the aircraft, increase the range and time, and improve the flight performance of the aircraft. The flexible beam propeller blades can reduce the drag generated by the engine and improve the speed and stability of the aircraft.
[0030] The present invention has been described in detail above. However, modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, any modifications or improvements that do not depart from the spirit of the present invention are within the protection scope of the present invention.
Claims
1. A bearingless rotor hub, comprising a hub central assembly (1), wherein a hub upper pressure plate (2) is disposed on the upper surface of the hub central assembly (1), and a bolt (3) is disposed on the upper surface of the hub upper pressure plate (2), wherein a nut (4) is threaded onto the outer surface of the bolt (3), characterized in that: The inner wall of the hub central component (1) is provided with a positioning assembly (7), which comprises: A positioning ring (701) is fixedly connected to the bottom of the inner wall of the hub central component (1), and the upper surface of the hub upper pressing plate (2) is fixedly connected with a reinforcing piece (702), and the bottom of the hub upper pressing plate (2) is fixedly connected with a positioning rod (703).
2. A bearingless rotor hub as claimed in claim 1, characterized in that: The position of the positioning rod (703) corresponds to the position of the positioning ring (701), and the size of the positioning rod (703) is adapted to the size of the positioning ring (701).
3. A bearingless rotor hub as in claim 1, wherein: The size of the hub upper pressing plate (2) is adapted to the size of the hub central component (1).
4. A bearingless rotor hub as in claim 1, wherein: The base of the hub central component (1) is a flange structure and has a reserved mounting bolt hole, and the reinforcing piece (702) is arranged in an X shape.
5. A flexible beam propeller comprising a propeller assembly (8), characterized by: The propeller assembly (8) comprises a propeller intermediate mounting section (801), the upper surface center of the propeller intermediate mounting section (801) is fixedly connected with a propeller metal bushing (802), the side of the propeller intermediate mounting section (801) is fixedly connected with a propeller flexible beam flapping deformation section (803), and the side of the propeller flexible beam flapping deformation section (803) is fixedly connected with a propeller airfoil section (804).
6. A flexible beam propeller according to claim 5, wherein: The size of the propeller intermediate mounting section (801) is adapted to the size of the hub central component (1), and the center of the propeller intermediate mounting section (801) corresponds to the position of the positioning ring (701).
7. A flexible beam propeller according to claim 5, wherein: The position of the propeller metal bushing (802) is at the center of the propeller intermediate mounting section (801), the number of the propeller flexible beam flapping deformation section (803) is two, and the two propeller flexible beam flapping deformation sections (803) are symmetrically arranged at the center of the propeller intermediate mounting section (801).