Multi-rotor UAV with detachable dual-propeller structure

A multi-rotor UAV, detachable technology, applied in the field of UAV, can solve the problem of low flight efficiency of multi-rotor UAV, and achieve the effect of high flight efficiency

Inactive Publication Date: 2018-09-07
武汉最近应急科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The invention provides a multi-rotor UAV with a detachable double-blade structure, which solves or partially solves the technical defect of low flight efficiency of multi-rotor UAVs in the prior art

Method used

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  • Multi-rotor UAV with detachable dual-propeller structure
  • Multi-rotor UAV with detachable dual-propeller structure
  • Multi-rotor UAV with detachable dual-propeller structure

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Embodiment Construction

[0040] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art belong to the scope of protection of the present invention; among them, the "and / or" keyword involved in the present embodiment means and, or both In other words, A and / or B mentioned in the embodiments of the present invention represent two situations of A and B, A or B, and describe the three states of A and B, such as A and / or B means: only include A but not B; only include B but not A; include A and B.

[0041] At the same time, in the embodiments of the present invention, when a component is referred to as being "fixed"...

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Abstract

The invention discloses a multi-rotor-wing unmanned aerial vehicle of a detachable twin-propeller structure, and belongs to the technical field of unmanned aerial vehicles. The multi-rotor-wing unmanned aerial vehicle comprises a first rotor wing, a second rotor wing, two quick detaching assemblies, a rotor wing power assembly fixed to a rotor wing shaft, a vehicle body and a signal positioning assembly. The first rotor wing is rotationally fixed to the rotor wing power assembly through one quick detaching assembly, and the second rotor wing is rotationally fixed to the rotor wing power assembly through the other quick detaching assembly. The diameter of the first rotor wing is larger than that of the second rotor wing. The signal positioning assembly is fixed to a vehicle shell. The technical defect that an existing multi-rotor-wing unmanned aerial vehicle is low in flight efficiency is overcome.

Description

Technical field [0001] The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a multi-rotor unmanned aerial vehicle with a detachable double-propeller structure. Background technique [0002] Unmanned aircraft is abbreviated as "unmanned aerial vehicle", which is an unmanned aircraft operated by radio remote control equipment and self-provided program control devices. There is no cockpit on board, but it is equipped with autopilot, program control device, information acquisition device and other equipment. The personnel on the ground, on the ship or the remote control station of the mother aircraft use radar and other equipment to track, locate, remotely control, remotely measure and digitally transmit it. It can take off like an ordinary airplane under radio remote control or launch with a booster rocket, or it can be carried into the air by a parent plane for flight. [0003] The UAV in the prior art includes a fuselage and a rotor...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): A63H27/133A63H27/18A63H27/20
CPCA63H27/001A63H27/12
Inventor 赵国成万勇赵涛
Owner 武汉最近应急科技有限公司
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