The invention relates to the technical field of unmanned helicopter rotor transmission structures, in particular to an unmanned helicopter rotor variable pitch hinge structure which comprises a support arm, wherein the inner end of the support arm is connected to a rotor shaft of a helicopter, and the outer end of the support arm is connected to a rotor; an inner end bearing assembly, a shaft sleeve assembly and an outer end bearing assembly are sequentially arranged on the supporting arm from the inner end to the outer end, an inner end fixing piece is arranged at the inner end of the supporting arm, an outer end abutting piece is arranged at the outer end of the supporting arm, and the inner end bearing assembly and the outer end bearing assembly are sleeved with a shell. The shell rotates along with the inner end bearing assembly and the outer end bearing assembly and is fixedly connected with the inner end fixing piece. According to the variable-pitch hinge structure, the bearing assembly structure on the supporting arm is optimized and improved, the shell is supported through the bearing assembly, loads on the shell can be shared through the simpler bearing assembly structure, and under the action of bearing the same centrifugal force and lift force, the variable-pitch hinge structure can be more stable, more reliable and longer in service life; and the economical efficiency and the safety of the helicopter are ensured.
本发明涉及无人机旋翼传动结构技术领域,具体涉及一种无人直升机旋翼变距铰结构,包括支臂,支臂的内端连接至直升机的旋翼轴,支臂的外端连接至旋翼;支臂上从内端往外端方向依次设置内端轴承组件、轴套组件和外端轴承组件,支臂的内端设置有内端固定件,支臂的外端设置有外端抵紧件,内端轴承组件和外端轴承组件上套设有壳体,壳体随内端轴承组件和外端轴承组件转动且壳体与内端固定件连接固定。本发明通过对支臂上的轴承组件结构进行优化改进,利用轴承组件进行壳体的支撑,可通过更为精简的轴承组件结构分担壳体上的载荷,在承受同等离心力和升力的作用下,本发明提供的变距铰结构能够更加稳定可靠,寿命更高,保证了直升机的经济性和安全性。
Unmanned helicopter rotor variable pitch hinge structure
一种无人直升机旋翼变距铰结构
2021-06-04
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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