Double-rotor-wing unmanned plane

Abstract

The invention discloses a double-rotor-wing unmanned plane. Flying control on the double-rotor-wing unmanned plane is realized based on a four-rotor-wing unmanned plane flying control principle by designing a single-degree-of-freedom automatic tilter, semi-rigidity rotor wings and a flying control system. The unmanned plane consists of a stander, a plane body, a power bin, rotor wing systems and a rotor wing system support, wherein the plane body is provided with an equipment bin in which a flight posture sensor group, a PID controller, a lithium battery and an electronic speed controller are arranged; the plane body, the power bin and the rotor wing system support are in rigid fixed connection through the stander; a brushless motor and a steering engine are arranged in the power bin; the steering engine drives a pull rod to operate the single-degree-of-freedom automatic tilter and control the rotor wings to periodically change the distance; the angle of the tilter is measured by a potentiometer, so that precise control is facilitated; the rotor wing systems are symmetrically arranged and are positioned on the same horizontal plane; the rotating directions of the rotor wings are opposite, and the rotor wings are mounted on a total distance hinge so as to be mechanically limited to do waving motion. According to the unmanned plane, the operation mechanism is simplified; the flying quality is good; the requirement on the precision of a theoretical model is low, and an extremely high practical value is achieved.

Description

technical field [0001] The invention relates to a dual-rotor UAV, in particular to a non-coaxial dual-rotor UAV using a semi-rigid blade and a single-degree-of-freedom automatic tilter. Background technique [0002] The patent of this invention is a new type of unmanned aerial vehicle designed and proposed based on the flight control principle of four-rotor unmanned aerial vehicle and the principle of periodic pitch change of the conventional helicopter tilter, and the swing of the rotor. The purpose is to solve the problem with a simpler mechanism and a more convenient and easy control system. The problem of complex control and manipulation of the current dual-rotor aircraft. [0003] The existing common non-coaxial dual-rotor aircraft (such as CH-47 "Chinook" helicopter, V-22 "Osprey" tilt rotor aircraft, etc.), its automatic tilter has three degrees of freedom, that is, it moves up and down along the z-axis The control of the collective pitch, the rotation control period...

AI Technical Summary

Problems solved by technology

This is not conducive to the simplification of the control model, but also increases the difficulty of problem research

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