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A composite wing UAV

A technology of unmanned aerial vehicles and compound wings, which is applied in the field of compound wing unmanned aerial vehicles, and can solve problems such as inconvenient loading and unloading and complex structure of UAVs.

Active Publication Date: 2019-07-02
北京尖翼科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] The technical problem to be solved by the present invention is to solve the problems of complex structure and inconvenient loading and unloading of existing drones

Method used

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  • A composite wing UAV
  • A composite wing UAV
  • A composite wing UAV

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Embodiment Construction

[0036] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0037]In the description of the present invention, it should be noted that unless otherwise specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection. Connected, or integrally connected; it can be mechanically conne...

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Abstract

The present invention relates to the field of aircraft technology, in particular to a composite wing unmanned aerial vehicle, comprising a wing-body fusion body, a fixed wing part, a multi-rotor part, a landing gear, a propeller and a power mechanism. The fixed wing part includes two fixed wings, two The fixed wings are separately arranged on both sides of the wing-body fusion; the multi-rotor part includes multiple sets of rotor mechanisms, and the multiple sets of rotor mechanisms are symmetrically arranged on both sides of the wing-body fusion. Each set of rotor mechanisms includes a connecting rod and a rotor. The fixed wing is connected, the rotor is horizontally arranged on the connecting rod, and the connecting rod is equipped with a mounting shaft perpendicular to the axial direction of the connecting rod, and the end of the mounting shaft is provided with a first slope; The matching connection hole is provided with a card slot on the hole wall of the connection hole, and a retractable buckle is arranged in the card slot, and a groove for matching with the retractable buckle is arranged on the installation shaft. The fixed-wing part and the multi-rotor part of the drone of the present invention can be quickly installed and disassembled without tools.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a compound wing unmanned aerial vehicle. Background technique [0002] Unmanned aircraft, referred to as "drone" for short, and "UAV" for English abbreviation, is an unmanned aircraft controlled by radio remote control equipment and its own program control device. From a technical point of view, it can be divided into: unmanned fixed-wing aircraft, unmanned multi-rotor aircraft, unmanned helicopter, unmanned parawing aircraft, etc. [0003] Fixed-wing aircraft rely on the thrust generated by propellers or turbine engines as the power for the aircraft to fly forward. The main lift comes from the relative motion between the fixed wing and the air. Therefore, the fixed-wing aircraft must have a certain relative air speed to fly normally. Based on this, fixed-wing aircraft generally have the advantages of fast flight speed, high flight altitude, and large load capacity. When there ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/00B64C27/08B64C27/26B64C39/10
CPCB64C1/00B64C27/08B64C27/26B64C39/10B64C2039/105B64U10/25B64U30/10B64U10/10B64U30/20
Inventor 丁未龙赵鑫李天真袁野
Owner 北京尖翼科技有限公司