Three-bypass propeller power-type vertical takeoff and landing fixed-wing unmanned aerial vehicle

An unmanned aerial vehicle, vertical take-off and landing technology, applied in vertical take-off and landing aircraft, aircraft, rotorcraft, etc., can solve the problems of affecting cruise efficiency, complex mechanism, high technical difficulty of tilting device, and achieve high redundancy of power system , The effect of high utilization rate of power system

Inactive Publication Date: 2018-05-08
湖北航天飞行器研究所
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Problems solved by technology

The tilting device of the tilting-rotor aircraft is technically difficult and the mechanism is complicated, so it is difficult to guarantee re

Method used

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  • Three-bypass propeller power-type vertical takeoff and landing fixed-wing unmanned aerial vehicle
  • Three-bypass propeller power-type vertical takeoff and landing fixed-wing unmanned aerial vehicle
  • Three-bypass propeller power-type vertical takeoff and landing fixed-wing unmanned aerial vehicle

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Embodiment Construction

[0025] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not constitute a conflict with each other.

[0026] Aiming at the problem that most of the existing aircraft cannot meet the requirements of high-efficiency cruising and level flight, vertical take-off and landing, and hovering in the air at the same time, the present invention provides a new type of fixed-wing unmanned aerial vehicle capable of vertical take-off and landing, which can realize vertical take-off and landing, and fixed-point ...

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Abstract

The invention discloses a three-bypass propeller power-type vertical takeoff and landing fixed-wing unmanned aerial vehicle and belongs to the field of unmanned aerial vehicles. The three-bypass propeller power-type vertical takeoff and landing fixed-wing unmanned aerial vehicle comprises a structural unit, power units and a flight control and avionics unit, wherein the structural unit comprises afuselage, a vertical tail, wings, a rudder, elevons and tail braces; the fuselage is located at the center of the entire unmanned aerial vehicle; one vertical tail and two wings are fixed on the fuselage, and have an included angle of 120 degrees relative to one another; the power units are arranged on wing tips of the vertical tail and the wings; the vertical tail is provided with the rudder; the wings are provided with the elevons; the tail braces are arranged on the vertical tail and the wings; and the flight control and avionics unit installed in a cavity inside the fuselage. The unmannedaerial vehicle system has low overall redundancy and high use efficiency, and can achieve vertical take-off and landing, fixed-point hovering in the air and high-efficiency cruising level flight.

Description

technical field [0001] The invention belongs to the general technical field of unmanned aerial vehicles, and more specifically relates to a fixed-wing unmanned aerial vehicle capable of vertical take-off and landing in a three-duct propeller power mode. Background technique [0002] Traditional unmanned aerial vehicles can be divided into two types: fixed-wing and rotary-wing aircraft. When the fixed-wing aircraft is flying, the lift is provided by the wings, and the flight time and range are relatively large. According to the difference in weight and size, the fixed-wing aircraft can choose to take off by hand throwing, ejection, taxiing, etc., and land and recover by hitting the net, parachuting, and taxiing. [0003] Generally speaking, the take-off and landing conditions of fixed-wing aircraft are relatively harsh. Rolling take-off or landing requires a relatively flat runway. Catapult take-off requires a special ejection device. navigation control system, etc. In add...

Claims

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Application Information

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IPC IPC(8): B64C29/02B64C27/26B64C19/00
CPCB64C19/00B64C27/26B64C29/02
Inventor 陈颂张紫龙黄飞周子鸣张达张华君李康伟刘青
Owner 湖北航天飞行器研究所
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