A gasoline-electric hybrid vertical take-off and landing forward-swept fixed-wing unmanned aerial vehicle

Abstract

The present invention relates to the technical field of unmanned aerial vehicles, and relates to an oil-electric hybrid vertical take-off and landing forward-swept fixed-wing unmanned aerial vehicle. At least one electric ducted fan engine is built in the front compartment of the nose; the rear fuselage has a built-in energy component and a load compartment, and the rear fuselage tail is provided with a propulsion propeller assembly, which is used to provide forward thrust to overcome the UAV when it is flying. The aerodynamic resistance; the wing assembly is installed on both sides of the rear fuselage in the form of forward swept wing; the empennage assembly is installed on the tail section of the rear fuselage; the vertical lift device assembly is an electric fan type, and the two vertical lift device assemblies are installed symmetrically On the left and right sides of the middle section of the rear fuselage; the UAV has many characteristics such as vertical take-off and landing, long-distance navigation, etc., realizes the integration of high-lift vertical take-off and landing and efficient horizontal flight, the integrated design of vertical lift system and fixed-wing layout, And the integrated control of rotor vertical lift and fixed wing lift.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a cargo unmanned aerial vehicle. Background technique [0002] With the maturity of UAV technology and the gradual increase of the low-altitude opening range in my country, the market demand for large and medium-sized carrier UAVs with long flight time and fast speed is becoming stronger and stronger. In order to meet the market's long-distance and fast transportation demand for cargo drones, a type of vertical take-off and landing fixed-wing drones has become the first choice. This type of UAV has vertical take-off and landing capabilities, long flight time and long range, and low requirements for take-off and landing sites. [0003] At present, the technical approaches for realizing vertical take-off and landing of fixed-wing aircraft (manned aircraft or unmanned aerial vehicle) mainly include tilting rotor layout, tailstock tilting layout, ducted fan layout, ...

AI Technical Summary

Problems solved by technology

[0006] Relying on quadrotors to generate vertical lift limits the total weight of the aircraft that can be achieved. The vertical lift system is completely independent from the aerodynamic layout of the UAV's fixed wing without fusion design. The vertical lift system is completely ineffective and unfavorable when the UAV is flying horizontally.

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