The invention discloses a control mechanism applicable to a non-coaxial small double-rotor unmanned aerial vehicle and a mounting structure of the control mechanism. The control mechanism comprises a flight control system tray, a main beam and rotor system pods, wherein the flight control system tray is positioned in the middle of the main beam; the rotor system pods are symmetrically arranged at the two ends of the main beam of the unmanned aerial vehicle; the rotors adopt positive and negative rotors, and the rotating directions are opposite; the revolving speed of the rotors is controlled by a motor; a steering engine and a pull rod system are controlled to drive an automatic bank unit with a single degree of freedom to be rotated, and further enable the rotor systems to be pitched periodically; a steel sheet spring is used for transmitting the rotor lift force, and the swing motion of the rotors is limited and utilized; the rotor system pods adopt panel joggle joint manner structures, and are used for mounting the steering system, the motor, the rotor systems and the like. The control mechanism can effectively control the flight, the pitching, the rolling and other postures of the double-rotor unmanned aerial vehicle, so that the double-rotor unmanned aerial vehicle is good in flight quality, suitable for design characteristics of the small unmanned aerial vehicle, simple in process and low in manufacturing cost.
Control mechanism of small double-rotor unmanned aerial vehicle and mounting structure of control mechanism
2015-05-13
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |