Unmanned aerial vehicle

Abstract

The embodiment of the invention discloses an unmanned aerial vehicle, which comprises a fuselage provided with a first accommodating cavity and a second accommodating cavity, wherein the first wing and the second wing are arranged on two sides of the fuselage; a first rotor wing assembly which is mounted on the first wing, wherein the first rotor wing assembly can rotate relative to the fuselage;the second rotor wing assembly is mounted on the second wing, and the second rotor wing assembly can rotate relative to the fuselage; the third rotor wing assembly comprises a third motor and a thirdpropeller connected with the third motor, and the third motor is installed in the first containing cavity and partially exposed out of the fuselage; a fourth rotor wing assembly which comprises a fourth motor and a fourth propeller connected with the fourth motor, wherein the fourth motor is installed in the second containing cavity and partially exposed out of the fuselage. The third motor and the fourth motor are partially exposed out of the fuselage, so that when the aircraft vertically takes off and lands or hovers, heat of the third motor and the fourth motor can be dissipated through thethird motor and the fourth motor, and meanwhile, when the aircraft horizontally flies on a fixed wing, the flight resistance can be reduced.

Description

Technical field[0001]The embodiment of the present invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle.Background technique[0002]Fixed-wing aircraft have the characteristics of long flight time and long range, but take-off and landing generally require long-distance taxiing runways, so there are greater restrictions on the operating environment. Some small fixed-wing aircraft use catapult take-off or hand-thrown take-off, and parachute assisted landing. Although no special runway is required, special catapult or professionally trained operators are required for take-off. Although the parachute can slow down when landing The impact force of the aircraft landing still has certain damage to the aircraft, which is obviously not an ideal way.[0003]In order to solve the above-mentioned problems of aircrafts, at present, there are aircrafts with two sets of spiral power systems with both horizontal and vertical directions. Durin...

AI Technical Summary

Problems solved by technology

[0004] The inventor of the present invention is in the process of realizing the present invention, considers the heat radiation problem of aircraft, finds: the motor that provides vertical lifting screw power system is all exposed, and this when aircraft realizes horizontal flight (being fixed-wing flight), will Generates a lot of flight resistance, which affects the flight time

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