Rotor wing unmanned aerial vehicle capable of approaching fast

An unmanned and fast rotor technology, applied in the field of unmanned aerial vehicles, can solve the problems of inconvenient rapid deployment, rapid use, high requirements for take-off and landing sites, slow flight speed, etc., to save space, compact overall size, Simplify the effect of manipulating components and controls

Pending Publication Date: 2018-11-13
西安君晖航空科技有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Rotary-wing UAVs can hover in the air and perform work over designated locations, but they have disadvantages such as short flight time and slow flight speed; fixed-wing UAVs fly fast and can complete work tasks in a large area in a short time, but Unable to hover, and has high requirements for take-off and landing sites, it is not convenient for quick deployment and quick use

Method used

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  • Rotor wing unmanned aerial vehicle capable of approaching fast
  • Rotor wing unmanned aerial vehicle capable of approaching fast
  • Rotor wing unmanned aerial vehicle capable of approaching fast

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Embodiment Construction

[0020] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0021] combined with figure 1 , figure 2 , image 3 , Figure 4 , Figure 5 , Figure 6 .

[0022] When the present invention is implemented in practice, a fast approaching rotor UAV includes a fuselage main body 1, a launching shell 13 and a launching device 16, and the top of the fuselage main body 1 is provided with a coaxial double blade device 2, The coaxial double paddle device 2 includes an inner shaft 3, the bottom of the inner shaft 3 is provided with a bevel gear 4, and the top position of the inner shaft 3 is provided with an upper rotating disk 5, and the inner shaft 3 The outer shaft 6 is socketed at the middle position, the bottom of the outer shaft 6 is provided with a bevel gear 2 7, the bevel gear 2 7 and the bevel gear 1 4 are arranged symmetrically, and the inner shaft 3 runs through the center of the bevel gear 2 7 The bevel gear t...

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Abstract

The invention discloses a rotor wing unmanned aerial vehicle capable of approaching fast. The rotor wing unmanned aerial vehicle comprises a fuselage body, a launching shell and a launching device, wherein a coaxial double-blade device is arranged at the top of the fuselage body; the coaxial double-blade device comprises an inner shaft, a first bevel gear is arranged at the bottom of the inner shaft, and an upper rotating disc is arranged on the top position of the inner shaft; an outer shaft is arranged in the middle part of the inner shaft in a sleeving connection mode, and a task device isarranged on the lower part of the fuselage body; the launching shell is matched with the fuselage body of foldable blades, the launching shell comprises two cambered-surface shells which are same in size, wherein the cambered-surface shells are connected with each other in a matched mode; and the launching device is internally provided with a launching cavity matched with the launching shell, andthe launching device is internally provided with a device for catapulting the launching shell. The rotor wing unmanned aerial vehicle overcomes the technical shortcomings of the prior art, has a reasonable structure, adopts coaxial propeller-reversing layout, has the foldable blades, and can quickly approach a target area for hovering or flight operation.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a rapidly approaching rotor unmanned aerial vehicle. Background technique [0002] At present, drone technology is developing rapidly, and many traditional industries have begun to slowly introduce the application of drones, promoting the intelligent upgrading of the industry. [0003] UAVs on the market are usually dominated by rotary-wing UAVs and fixed-wing UAVs. Rotary-wing UAVs can hover in the air and perform work over designated locations, but they have disadvantages such as short flight time and slow flight speed; fixed-wing UAVs fly fast and can complete work tasks in a large area in a short time, but It cannot hover, and has high requirements on the take-off and landing site, so it is not convenient for quick deployment and quick use. [0004] In actual use, if the drone needs to approach the work area at high speed and then hover for work, a new type...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/10B64C1/00B64C1/30B64C27/50
CPCB64C27/10B64C1/00B64C1/30B64C27/50
Inventor 张冰融潘祈帆陈希平
Owner 西安君晖航空科技有限公司
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