2results about How to "Mechanically simple" patented technology

This invention discloses a heterogeneous multi-rotor layout with a single main rotor and partially tilted multiple slave rotors, relating to the field of unmanned aerial vehicle (UAV) design technology. It includes a large main rotor providing primary lift and n control rotors arranged around it, with some control rotors mounted horizontally and the rest tilted at a fixed angle. During steady-state flight, the anti-torsional torque of the main rotor is statically balanced by the horizontal component torque of the pull force from the tilted slave rotors. Attitude control of the UAV is achieved by differentially adjusting the rotational speeds of the control rotors, including pitch control, roll control, and yaw control. Pitch and roll control are achieved by differentially adjusting the rotational speeds of symmetrically positioned control rotors, while yaw control is achieved by differentially adjusting the rotational speeds between the horizontally mounted and tilted control rotor groups. This invention achieves a fusion of high aerodynamic efficiency and easy operation, effectively improving the UAV's endurance and flight performance.

The invention discloses a single main rotor-partially inclined multi-slave rotor heterogeneous multi-rotor layout, and relates to the technical field of unmanned aerial vehicle aircraft design, the single main rotor-partially inclined multi-slave rotor heterogeneous multi-rotor layout comprises a large-size main rotor providing main lift force and n control rotors arranged around the large-size main rotor, part of the control rotors are horizontally mounted, and the rest are obliquely mounted at a fixed angle; during steady-state flight, the reverse torsional moment of the main rotor is statically balanced by the horizontal component moment of the pulling force of the inclined slave rotor, attitude control is carried out on the unmanned aerial vehicle by carrying out differential adjustment on the rotating speed of the control rotor, and attitude control comprises pitching control, rolling control and yaw control. Wherein the pitching control and the rolling control are realized by differentially adjusting the rotating speed of the control rotors at symmetrical positions, and the yaw control is realized by differentially adjusting the rotating speed between the horizontally mounted control rotor group and the obliquely mounted control rotor group; according to the invention, the integration of high aerodynamic efficiency and simple control is realized, and the cruising ability and flight performance of the unmanned aerial vehicle are effectively improved.