Control mechanism of small double-rotor unmanned aerial vehicle and mounting structure of control mechanism

Abstract

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.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a control mechanism and its installation structure specially suitable for non-coaxial small-sized dual-rotor unmanned aerial vehicles. Background technique [0002] The research of non-coaxial dual-rotor UAV is one of the most important research links in the field of aviation aircraft design. It not only has certain practical value, but also is one of the key technologies that must be mastered in the development of tilt-rotor aircraft. The Chinese invention patent CN201410453204.0 "a dual-rotor UAV" applied by the applicant discloses a non-coaxial dual-rotor UAV, which can effectively control the unmanned aerial vehicles by adjusting the speed of the rotor system and changing the pitch of the rotor cycle. The heading, pitch and roll of the aircraft, the principle is as follows figure 1 , 2 , 3. The characteristics of this scheme are: based on the existing helicopter cyc...

AI Technical Summary

Problems solved by technology

[0003] However, for small UAVs, their design is often constrained by realistic conditions such as cost and process means, resulting in the design methods and structural characteristics of small UAVs being different from those of medium and large UAVs.

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