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Foldable protective unmanned aerial vehicle

A technology of unmanned aerial vehicle and protective frame, applied in the field of unmanned aerial vehicle, can solve the problems of poor convenience of use and low power efficiency, and achieve the effect of ensuring the convenience of use

Pending Publication Date: 2020-06-16
SHENZHEN GRIDMORE CREATIVE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the embodiment of the present application is to provide a foldable protective UAV to solve the problems of poor convenience of use and low power efficiency caused by the installation of the rotor protection frame of the existing miniature multi-rotor UAV before take-off

Method used

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  • Foldable protective unmanned aerial vehicle
  • Foldable protective unmanned aerial vehicle
  • Foldable protective unmanned aerial vehicle

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0043] An embodiment UAV of this embodiment group such as figure 1 , figure 2 As shown, the drone includes a first component 100 , a second component 200 , a first rotating mechanism 300 and a main power unit 400 .

[0044] The first assembly 100 is an L-shaped structure, including a fuselage body 110 and a machine arm 120 , and the fuselage body 110 and the machine arm 120 are distributed in an L shape. The inside of the fuselage body 110 can place batteries, main control circuit boards, flight controllers, wireless communication modules, etc., and has a relatively large weight. The above-mentioned modules inside the fuselage body 110 belong to the prior art, and will not be repeated in this application.

[0045] The second assembly 200 includes a rotor shield frame 210 . The second assembly 200 is rotatably connected to the machine arm 120 through the first rotating mechanism 300 .

[0046] The main power plant 400 includes a first rotor system 410, a rotation controller...

Embodiment 2

[0056] An embodiment UAV of this embodiment group such as Figure 5 As shown, it includes a first assembly 100 , a second assembly 200 , a first rotating mechanism 300 and a main power device 500 .

[0057] The first assembly 100 is an L-shaped structure, including a fuselage body 110 and a machine arm 120 . The interior of the main body 110 of the fuselage can place batteries, main control circuit boards, flight controllers, wireless communication modules, etc., and has a relatively large weight.

[0058] The second assembly 200 includes a rotor shield frame 210 . The second component 200 is connected to the arm 120 through the rotation of the first rotation mechanism 300 , and the rotation of the first rotation mechanism 300 realizes the folding and unfolding of the UAV, and there is no need to disassemble the rotor protection frame 210 when folding the UAV. The first rotating mechanism 300 may be a hinged structure, or a shafting structure.

[0059] The main power device...

Embodiment 3

[0065] The UAV of this embodiment group also includes a second driver, the second driver is arranged on the first assembly or the second assembly, and outputs the torque that makes the UAV rotate around the third axis; the third axis is different from the first axis vertical.

[0066] An embodiment UAV of this embodiment group such as Image 6 As shown, the drone includes a first component 100 , a second component 200 , a first rotating mechanism 300 , a main power device 400 , and a second driver 600 . Wherein, the first assembly 100, the second assembly 200, the first rotating mechanism 300 and the main power device 400 are related to figure 1 The drone shown is the same. The first driver (431, 432) outputs the torque that makes the UAV rotate around the X axis (ie the second axis), and its working principle is the same as that of figure 1 The first drivers of the drone are the same, but the setting positions are different, and they are set on the fuselage main body 110 ....

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Abstract

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a foldable protective unmanned aerial vehicle. The foldable protective unmanned aerial vehicle comprises a first assembly and a second assembly which are rotationally connected through a first rotating mechanism, and folding and unfolding of the unmanned aerial vehicle can be completed through rotation of the first rotating mechanism. The second assembly comprises the rotor wing protection frame, and the rotor wing protection frame does not need to be disassembled when the unmanned aerial vehicle is folded, so that the unmanned aerial vehicle has safety, Meanwhile, portability and use convenience are guaranteed. The flight control mode of the unmanned aerial vehicle is different from thatof a multi-rotor unmanned aerial vehicle, a main power device of the unmanned aerial vehicle can be configured to be a mode of a first rotor system, a rotation controller and a first driver, and rotors are fixed in distance; alternatively, the main power device may be configured in the manner of a second rotor system, where at least one rotor is variable pitch. Compared with a multi-rotor unmannedaerial vehicle with the same size, the unmanned aerial vehicle is large in rotor size and high in power supply efficiency, and the size of the unmanned aerial vehicle can be smaller while the endurance time is guaranteed.

Description

technical field [0001] The application belongs to the technical field of unmanned aerial vehicles, and in particular relates to a foldable protective unmanned aerial vehicle. Background technique [0002] In recent years, with the development of microelectronics technology and new materials, consumer drones (mainly helicopter drones) have developed rapidly. Early consumer drones mainly include two types: coaxial dual-rotor and single-rotor with tail rotor. In recent years, multi-axis drones, mainly quadrotor drones, have become the mainstream of the market. [0003] However, compared with traditional helicopters, multi-rotor UAVs have smaller rotors, especially micro UAVs. Due to the small size of the whole machine, the size of the rotors is small. The smaller size means low power efficiency and high noise. Therefore, the battery life of the micro UAV will be shorter. In addition, the main application of micro-UAVs is to take pictures. When taking pictures, the UAV is usu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/30B64C11/30B64D45/00
CPCB64C1/30B64C11/30B64D45/00B64U10/13B64U50/19B64U2101/30
Inventor 杨超峰
Owner SHENZHEN GRIDMORE CREATIVE TECH CO LTD
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