Multi-axis fixed-wing composite unmanned aerial vehicle and flight control method

A technology of fixed-wing and drones, applied in the field of drones, can solve the problems of fuselage structure limitations and slow flight speed

Pending Publication Date: 2019-01-04
SHENZHEN QIKER INTELLIGENT TECH CO LTD
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0003] The main purpose of the present invention is to propose a multi-axis fixed-wing composite unmanned aerial vehicle, aiming to solve the problem in the prior art that the multi-axis unmanned aerial vehicle is not flying fast due to the limitation of the fuselage structure

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  • Multi-axis fixed-wing composite unmanned aerial vehicle and flight control method
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  • Multi-axis fixed-wing composite unmanned aerial vehicle and flight control method

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Embodiment Construction

[0032] Embodiments of the present invention will be described in detail below, examples of which are shown in the drawings, wherein like reference numerals designate like elements or elements having the same function throughout. The embodiments described below by referring to the accompanying drawings are exemplary and are intended to explain the present invention, but cannot be construed as limitations to the present invention. Based on the embodiments in the present invention, those skilled in the art do not make creative work premise All other embodiments obtained below all belong to the protection scope of the present invention.

[0033] In order to solve the above technical problems, the present invention proposes a multi-axis fixed-wing composite unmanned aerial vehicle, referring to figure 1 and figure 2 , the multi-axis fixed-wing composite UAV includes a fixed-wing body 10, a rotor mechanism 20, and a steering mechanism 30 arranged in the fixed-wing body 10; the ste...

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Abstract

The invention discloses a multi-axis fixed-wing composite unmanned aerial vehicle which comprises a fixed wing body, a rotor mechanism and a steering mechanism arranged in the fixed wing body, whereinthe steering mechanism comprises a steering rod and a rotary drive component; the steering rod transversely penetrates through the fixed wing body and extends out from the two ends of a wing; the rotary drive component is used for driving the steering rod to rotate by taking an axis as a rotating shaft; the rotor mechanism comprises fixed supports, drive parts and rotors; the fixed supports are respectively and symmetrically arranged at the two ends of the steering rod; the drive parts are arranged on the fixed supports in the direction perpendicular to the steering rod; the rotors are connected with output shafts of the drive parts; rotating shafts of the rotors are mutually parallel and are vertically arranged with the steering rod. The multi-axis fixed-wing composite unmanned aerial vehicle disclosed by the invention solves the problem that in the prior art, a multi-axis unmanned aerial vehicle is low in flight speed due to unmanned aerial vehicle body structure restrictions.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a multi-axis fixed-wing composite unmanned aerial vehicle and a flight control method thereof. Background technique [0002] When a fixed-wing aircraft or UAV is flying horizontally, the lift generated by the pressure difference formed by the air flowing through the upper and lower wing surfaces allows the aircraft to use a smaller thrust engine to obtain a longer time in the air. However, fixed-wing aircraft require longer runways for takeoff and landing. The fixed-wing UAV equipped with a vertical take-off and landing rotor can better solve the problem that the fixed-wing UAV needs a runway run-up to take off and land, but in the level flight state, the rotor used for take-off and landing no longer functions. Instead, it becomes a burden that adds useless loads to the aircraft and brings flight resistance. In the prior art, multi-axis drones generally achieve level fli...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/22
CPCB64C27/22
Inventor 陈翔斌王敏
Owner SHENZHEN QIKER INTELLIGENT TECH CO LTD
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