The invention discloses a helicopter rotor variable pitch pull rod with actively adjustable rigidity and damping, and relates to the technical field of active vibration reduction of helicopter rotors. While the requirements for supporting and vibration reduction are met, coaxial arrangement of the vibration reduction direction and the center of the piezoelectric actuator is achieved, and various adverse effects caused by unbalanced centrifugal force can be effectively avoided. The variable-pitch pull rod sequentially comprises an upper hanging lug, an upper cover, an outer sleeve, a spring and a lower hanging lug from top to bottom. A pair of piezoelectric actuators coaxial with the spring is arranged in the outer sleeve, and a wedge-shaped structure part is arranged between the pair of piezoelectric actuators; the inner core shaft penetrates through the lower cover, the outer sleeve, the wedge-shaped structure part and the pair of piezoelectric drivers, and the wedge-shaped structure part is pressed by the piezoelectric drivers, so that the clamping force applied to the middle part of the inner core shaft is changed. Through the integrated design, vibration reduction in different flight states is achieved in the application field of the variable pitch pull rod of the helicopter, the vibration reduction effect is good, and the application range is wide.
本发明公开了一种刚度阻尼主动可调的直升机旋翼变距拉杆,涉及直升机旋翼主动减振技术领域。在满足兼顾支撑以及减振要求同时,实现了减振方向与压电促动器中心的同轴布置,可以有效避免不平衡的离心力带来的种种不利影响。所述变距拉杆从上到下依次包括的上挂耳、上盖、外套筒、弹簧以及下挂耳;在外套筒内部设有与弹簧同轴布置的一对压电驱动器,在一对压电驱动器之间设有楔形结构部;所述内芯轴贯穿下盖、外套筒、楔形结构部及一对压电驱动器,通过压电驱动器压迫楔形结构部,从而改变施加在内芯轴中部的夹紧力。通过一体化集成化设计实现在直升机变距拉杆应用领域实现不同飞行状态下的减振,减振效果好、适用范围广泛。
Helicopter rotor variable pitch pull rod with actively adjustable rigidity and damping
一种刚度阻尼主动可调的直升机旋翼变距拉杆
2024-10-15
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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