Vertical take-off and landing unmanned aerial vehicle

A technology of vertical take-off and landing and unmanned aerial vehicles, which is applied in the direction of vertical take-off and landing aircraft, unmanned aircraft, rotorcraft, etc., and can solve the problems of low rotor efficiency and high power consumption

Pending Publication Date: 2017-06-13
BEIJING FALCON UAV TECH CO LTD
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, the efficiency of the rotor directly connected to the power system is far inferior to that of the fixed-wing aircraft, so the power consumption is large

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  • Vertical take-off and landing unmanned aerial vehicle

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Embodiment Construction

[0019] The technical solutions of the present invention will be further described in detail below in conjunction with specific embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, and are not intended to limit the present invention.

[0020] In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", " The orientations or positional relationships indicated by "vertical", "horizontal", "top", "bottom", "inner" and "outer" are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and Simplified descriptions, rather than indicating or implying that the device or element referred to must have a particular way, be constructed and operate in a particular orientation, and thus should not be construed as limiting...

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Abstract

The invention provides a vertical take-off and landing unmanned aerial vehicle. The vertical take-off and landing unmanned aerial vehicle comprises a vehicle body (1). Canards (2) and rotor wing power sets (5) are arranged on the two sides of the front end of the vehicle body (1) symmetrically. Main wings (3) and wing power sets (5) are arranged on the two sides of the rear end of the vehicle body (1) symmetrically. A fixed wing power set (4) is arranged at the tail of the vehicle body (1). The vertical take-off and landing unmanned aerial vehicle combines the advantages of a fixed wing unmanned aerial vehicle and the vertical take-off and landing unmanned aerial vehicle, a canard type wing body combined fixed wing aircraft is selected as a main body, the canards and an aircraft main wing main beam serve as rotor wing and fixed wing aircraft joint main force bearing components, installation of four rotor wings is completed, and the vertical take-off and landing unmanned aerial vehicle with excellent aerodynamic layout is achieved finally. Through the vertical take-off and landing function, the unmanned aerial vehicle can take off without a runway, and the canard type layout fixed wing aircraft had endurance longer than that of a common rotor wing.

Description

technical field [0001] The invention belongs to the technical field of industrial-grade unmanned aerial vehicles, in particular to a vertical take-off and landing unmanned aerial vehicle. Background technique [0002] The fixed-wing aircraft that are common in the aviation field mainly rely on the wings to generate lift to balance the weight of the aircraft, and the power system is mainly used to overcome the flight resistance of the aircraft. Therefore, the power much smaller than the weight of the aircraft can lift the fixed-wing aircraft off the ground. The speed is relatively fast, and the voyage and cruise time are also long, but the take-off and landing distance is long, requiring high-quality runways, which seriously affects and hinders the application of fixed-wing aircraft in remote areas without dedicated airports. [0003] Rotary-wing helicopters, which are common in the aviation field, can solve the problem of vertical take-off and landing in small places. In th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/22B64C29/00
CPCB64C27/22B64C29/0008B64U10/00B64U30/20
Inventor 赖雪聪李刚伍可炳
Owner BEIJING FALCON UAV TECH CO LTD
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