The invention discloses a minitype co-shaft double-rotor wing unmanned aerial vehicle based on an oscillation damping rotor wing. The minitype co-shaft double rotor wing unmanned aerial vehicle based on the oscillation damping rotor wing comprises a fuselage body, a double-ring upper structure body, a double-ring lower structure body, and a fastening piece, wherein the double-ring upper structure body and the double-ring lower structure body are same in structure and are arranged in a manner of being symmetrical about the fuselage body in an up-down direction; and the fastening piece is applied for arranging a first torquer and a first angle sensor between an upper inner ring and an upper outer ring and also is applied for arranging a second torquer and a second angle sensor between a lower inner ring and a lower outer ring. The double-ring structure bodies in the unmanned aerial vehicle can be used for effectively isolating the influence of the vibration source rotor wing on the fuselage body. The angle sensors are used as sensitive elements for the vibration of the rotor wing; the torquers are used as actuator executing mechanisms; the angle sensors are sensitive with deflection angles caused by the vibration of blades of the rotor wing; the deflection angles can be treated by a control unit of the unmanned aerial vehicle to convert into torque required to be output by the torquers so as to enable the deflection angles caused by the vibration to be zero, so that the influence of the vibration of the blades of the rotor wing on the fuselage body can be effectively isolated.
Minitype co-shaft double-rotor wing unmanned aerial vehicle based on oscillation damping rotor wing
2016-01-20
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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