multicopter

Abstract

The invention discloses a multi-rotor aircraft. The multi-rotor aircraft comprises a body, an even number of supporting arms, forward rotors and reverse rotors, wherein the forward rotors and the reverse rotors are alternately fixed at one end, far away from the body, of each supporting arm; the body comprises a first reference plane; the supporting arms are radially fixed around the body, are in central symmetry relative to the body, and extend along a plurality of first axes respectively; a first included angle of 2 to 45 degress is formed between each first axis and the first reference plane; the first axes are positioned on a second reference plane; a dihedral angle between the second reference plane and the first reference plane is the first included angle; rotary shafts of the forward rotors are perpendicular to a third reference plane; the third reference plane is positioned on one side, opposite to the first reference plane, of the second reference plane; a dihedral angle between the third reference plane and the second reference plane is a second included angle of 0 to 10 degree; the rotary shaft directions of the reverse rotors and the rotary shaft directions of the forward rotors are in mirror symmetry. By inclining the rotary shafts of the forward rotors and the reverse rotors, the component force of lifting force in the direction of reverse torsion force is obtained, so that the reverse torsion force is enhanced, and the response speed in a rotation process is increased.

Description

technical field [0001] The invention relates to an aircraft, in particular to a multi-rotor aircraft. Background technique [0002] At present, multi-rotor UAVs are driven by multiple independent motors, for example, a quadrotor aircraft is driven by four independent motors. The thrust generated by the rotor UAV can better achieve static hovering, and can change its attitude in a short period of time while suspended in the air, and has a high degree of maneuverability and effective carrying capacity. [0003] The rotation of the existing multi-rotor unmanned aerial vehicle relies on the reverse torque difference generated by the forward and reverse rotation propellers to drive the direction angle of the aircraft to change. Due to the limited magnitude and response of the anti-torque force, for an aircraft with a relatively large inertia, the driving force of the direction angle is relatively weak, resulting in a slow response speed during the rotation of the multi-rotor UAV...

AI Technical Summary

Problems solved by technology

Due to the limited size and response of the anti-torque force, for the aircraft with relatively large inertia, the driving force of the direction angle is relatively weak, resulting in a slow response speed during the rotation of the multi-rotor UAV

At the same time, due to the inability to respond quickly, when there is external disturbance such as wind, it takes a relatively long time to adjust the balance, and the ability to resist disturbance is not strong

Images