Unmanned aerial vehicle (UAV) and manufacturing method of fuselage shell of unmanned aerial vehicle

Abstract

The invention discloses an unmanned aerial vehicle (UAV). The UAV comprises a solar cell, a coaxial motor, an upper rotor, a lower rotor, a working part, a stabilizing rotor and a load part. Through the arrangement of the three rotors, the load capacity of the UAV is greatly improved. With the improvement of the load capacity, the function of the load part can be increased, that is, the UAV has avariety of functions and effects. The upper rotor generates air flow during operation, a stable precompression layer with fast and high gas density airflow is formed on the lower rotor, and the operation of the lower rotor is more efficient and smooth, so that high mobility and high stability are achieved. The direction of the UAV is controlled by the joint control over the angle of the coaxial motor by a first steering engine and a second steering engine, and a pendulum angle is in the vertical direction due to the control of the first steering engine and the second steering engine, so that the UAV makes fine directional operation, and the solar cell is installed to improve the cruising power of the UAV. The invention further discloses a manufacturing method of an UAV shell.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a method for manufacturing an unmanned aerial vehicle and its fuselage shell. Background technique [0002] At present, most coaxial helicopters, also known as coaxial anti-propeller helicopters, share a drive shaft with double-layer blades, but the rotation direction is opposite, which not only balances the one-way rotation deflection moment, but also provides With the "pre-compression", the second stage has a larger "intake / exhaust volume" and "airflow density". Although the effect cannot be doubled, the improvement is obvious. During the research process, the inventor found that the traditional coaxial helicopter has at least the following disadvantages: the lifting speed is relatively slow; [0003] The upper rotor and the lower rotor of a practical coaxial rotor helicopter usually have two blades respectively, and can only be set to three blades at most. Due to the ...

AI Technical Summary

Problems solved by technology

The inventor found during the research process that the traditional coaxial helicopter has at least the following disadvantages: the lifting speed is slow; the use effect is poor; the energy loss of sharing a transmission shaft is large

Due to the limited number of rotors, the lift of the helicopter is hindered, and the possibility of further enlargement of the coaxial rotor counter-rotating helicopter is also restricted.

At the same time, due to the limited number of rotors, in order to ensure the lift, the arm span of the rotors can only be increased. As a result, the upper rotor and the lower rotor are likely to collide during large-scale maneuvering flight, resulting in flight accidents.

Moreover, due to the long shaft and long rotor, the increase in structural weight caused by the complexity of the control device has also offset the advantages of the coaxial rotor counter-rotating helicopter

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