The invention discloses a heavy-load low-structure-complexity double-coaxial-twin-rotor unmanned aerial vehicle, wherein rotor transmission mechanisms are arranged at the left side and the right side of a vehicle body of an unmanned aerial vehicle body; through transmission mechanisms arranged on the unmanned aerial vehicle body, power is transmitted to the rotor transmission mechanisms arranged at the two sides of the unmanned aerial vehicle body through driving shafts; the rotor transmission mechanisms transmit the power to an upper rotor and a lower rotor through an upper rotor transmission rod and a lower rotor transmission rod via the transmission among four mutually engaged bevel gears; and the identical-rotating-speed and opposite-direction rotation of the upper rotor and the lower rotor is realized. A total variable-pitch mechanism is arranged between the upper rotor transmission rod and the upper rotor, and the regulation of the pitch angle and the roll angle of the unmanned aerial vehicle is realized; a variable-total-pitch mechanism is arranged between the lower rotor transmission rod and the lower rotor, the regulation of the total pitch of the unmanned aerial vehicle is realized; and the yaw angle and the total lift of the unmanned aerial vehicle are controlled. The heavy-load low-structure-complexity double-coaxial-twin-rotor unmanned aerial vehicle has the advantages that the characteristics of heavy effective load and high output power are realized; and a redundancy design method is adopted, and the flight stability of the unmanned aerial vehicle is improved through the design of multiple rotors and multiple sets of variable-pitch mechanisms.
Heavy-load low-structure-complexity double-coaxial-twin-rotor unmanned aerial vehicle
2015-08-26
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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