Micro coaxial double-rotor wing unmanned aerial vehicle

Abstract

The invention relates to the technical field of aircrafts, in particular to a micro coaxial double-rotor wing unmanned aerial vehicle. The unmanned aerial vehicle comprises a shell; a load mechanism is mounted at the bottom end in the shell; the load mechanism comprises a loading holder; a rotating base is arranged on the inner side of the loading holder, and is rotationally connected with the loading holder through a connecting shaft; a camera is fixedly mounted on the side wall of the rotating base; a power mechanism is arranged at the bottom end of the loading holder, and comprises a secondfixed plate; the second fixed plate is fixedly connected with the loading holder; a battery is fixedly mounted at the top of the second fixed plate; connecting columns are arranged in four-angle positions of the second fixed plate, and are fixedly mounted on the second fixed plate; a flight control board is fixedly mounted at the top of the battery; a transmission mechanism is arranged at the topend of the flight control board; an operation mechanism is mounted at the top ends of the connecting columns; and rotor wing mechanisms are arranged at the top end of the operation mechanism. The unmanned aerial vehicle is compact in structure, high in controllability and high in maneuverability.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a miniature coaxial double-rotor unmanned aerial vehicle. Background technique [0002] The miniaturization of aircraft is an aspect pursued by many researchers and users. It can adapt to every corner of the battlefield in the military field, and at the same time, it is flexible and difficult to be found. For exploration and search and rescue work, at present, the aircraft is generally a multi-rotor unmanned aerial vehicle. However, due to the complexity of the parts of the multi-rotor unmanned aerial vehicle and the increased load, this increases the moment of inertia during the transition of the flight state and reduces the controllability of the aircraft. sex and mobility. Contents of the invention [0003] The purpose of the present invention is to solve the shortcomings of low maneuverability and controllability in the prior art, and propose a miniature coaxial double-ro...

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to solve the shortcomings of low maneuverability and controllability in the prior art, and propose a miniature coaxial double-rotor UAV

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