一种可减弱复合式飞行器挥舞角度的桨毂
By introducing a flapping shaft and elastic bearing assembly into the rotor hub design of the compound aircraft, the structural vibration and fatigue problems caused by rotor flapping were solved, resulting in more stable flight performance.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- YIWEITE (NANJING) AVIATION TECH CO LTD
- Filing Date
- 2025-09-18
- Publication Date
- 2026-07-17
Smart Images
Figure CN224511450U_ABST
Abstract
Claims
1. A hub for reducing the flap angle of a composite aircraft, comprising: The device includes a hub assembly for fixing the blades together. The hub assembly includes a hub mounting base, a blade mounting base rotatably connected to the hub mounting base, a flapping shaft inserted between the hub mounting base and the blade mounting base, bearings symmetrically arranged on both sides of the hub mounting base, and a flexible bearing assembly for limiting the rotation angle of the flapping shaft. Both ends of the flapping shaft are connected to the bearings and the flexible bearing assembly.
2. A hub for reducing the drag of a compound aircraft, as in claim 1, wherein: Each of the aforementioned elastic bearing assemblies includes an elastic bearing housing fixedly connected to the propeller hub mounting base, an elastic bearing inner core housed within the elastic bearing housing, and an elastic bearing filler disposed between the elastic bearing housing and the elastic bearing inner core, the elastic bearing inner core being interconnected with the swing shaft.
3. A hub for reducing the drag of a compound aircraft, as in claim 2, wherein: The elastic bearing housing is provided with multiple limiting grooves, and one end of the elastic bearing inner core is provided with multiple limiting ends, each of the limiting ends being accommodated in the limiting groove.
4. A hub for reducing the drag of a compound aircraft, as in claim 3, wherein: The outer contour formed by the arrangement of multiple limiting grooves and the outer contour formed by the arrangement of multiple limiting ends are both cross-shaped.
5. A hub for reducing the drag of a compound aircraft, as in claim 3, wherein: Each of the limiting grooves accommodates a limiting end and is in clearance fit, with the gap between the limiting groove and the limiting end being consistent.
6. A hub for reducing the drag of a compound aircraft, as in claim 1, wherein: The elastic bearing assembly is connected to the swing shaft by a spline.
7. A hub for reducing the drag of a compound aircraft, as in claim 1, wherein: The axial directions of the two elastic bearing assemblies are on the same straight line, which is the flapping axis of the propeller hub, and the angle between the line connecting the first and second propeller blades and the flapping axis is less than 90 degrees.
8. A hub for reducing the drag of a compound aircraft, as in claim 1, wherein: The propeller hub mounting base includes a propeller hub base and propeller hub side plates fixedly connected to both sides of the propeller hub mounting base.
9. A hub for reducing the drag of a compound aircraft, as in claim 1, wherein: The blade and the blade mounting base are integrally formed, or the blade and the blade mounting base are fixedly connected by bolts.
10. A hub for reducing the drag of a compound aircraft, as in claim 1, wherein: The rotor hub, which can reduce the flapping angle of the compound aircraft, also includes a rotor shaft fixedly connected to one side of the rotor hub assembly.