The invention discloses a flapping wing turnover mechanism, and belongs to the field of micro aircrafts. The invention is used for the flapping rotor aircraft. The flapping rotor aircraft comprises a rotating shaft sleeve, a fuselage frame, a servo motor driving part, a turntable part, a cross rod, a flapping wing bracket part, a right flapping wing, a left flapping wing, a flapping wing turnover mechanism, a pull wire and a flapping wing rotating shaft part. The flapping wing turnover mechanism body is used for completing flapping wing turnover by taking sudden change of inertia force and centrifugal force as a main driving force source when the flapping rotor aircraft is switched in different motion modes. According to the invention, the abrupt change of inertia force and centrifugal force during the conversion of different motion modes of the flapping-rotor aircraft is used as a main driving force source to complete flapping-wing overturning, and the reduction of mechanical efficiency caused by the installation of a servo motor at the flapping end of the flapping-wing mechanism is avoided. According to the invention, the conversion of different flapping modes of the flapping wings is realized through flapping wing overturning, so that the flapping-rotor aircraft can realize the optimal torsion angle amplitude in different motion modes, and the flight efficiency of the flapping-rotor aircraft is further improved.
本发明公开的一种扑翼翻转机构,属于微型飞行器领域。本发明用于扑旋翼飞行器。所述扑旋翼飞行器包括转轴套管、机身框架、伺服电机驱动件、转盘部件、横杆、扑翼支架部件、右侧扑翼、左侧扑翼、扑翼翻转机构、拉线、和扑翼转轴部件。所述扑翼翻转机构本体用于扑旋翼飞行器在不同运动模式转换时的惯性力和离心力突变作为主要驱动力源完成扑翼翻转。本发明通过扑旋翼飞行器在不同运动模式转换时的惯性力和离心力突变作为主要驱动力源完成扑翼翻转,避免扑翼机构的拍动端安装伺服电机导致机械效率的降低。本发明通过扑翼翻转实现扑翼不同拍动模式的转换,使扑旋翼飞行器能够在不同运动模式下实现扭转角幅度最优,进而提高扑旋翼飞行器的飞行效率。
Flapping wing turnover mechanism
一种扑翼翻转机构
2024-09-20
Patent
Electronic Resource
Chinese
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