Machine arm quick-release structure for multi-rotor unmanned aerial vehicle

A technology of multi-rotor unmanned and aircraft-used aircraft, applied in the direction of rotorcraft, unmanned aircraft, fuselage, etc., can solve the problems of non-detachable, large storage space, waste of space, etc., to achieve convenient portability and transportation, guarantee The effect of expanding speed and reducing storage volume

Pending Publication Date: 2019-01-18
SHANGHAI BOONRAY INTELLIGENT TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Among the existing miniature multi-rotor UAVs, when the wheelbase reaches about 1m, for the convenience of accommodation, the folding arm is often the first choice for this type of model, and there are also some cases where the arm and the frame are directly connected for protection reasons. It is fixed and cannot be disassembled, and the storage boxes of these models are too large to be stored in some small cars with small trunks
[0003] For existing miniature multi-rotor UAVs, the size of the overall flight control system components that provide the working flight control of the source blades is not large, even if the size of the power battery is included, it still does not take up too much volume, and its lift space is The most space-consuming part of the entire multi-rotor drone. For a multi-rotor drone with a wheelbase of about 1m, fixing the arm on the frame will undoubtedly take up a lot of storage space. In order to avoid the vertical vibration of the arm Due to the influence of the mechanism, the folding arm often adopts the form of vertical folding, and this folding method will have to increase the height of the tripod due to the length of the arm, which wastes a certain space in the height of the fuselage; for aerial survey In the field, in order to ensure that the camera does not capture the tripod when shooting, it is necessary to reduce the height of the camera in the drone as much as possible. After the tripod is increased to ensure that the camera is low enough, the mounting frame for fixing the camera also needs to be lengthened, which will cause unnecessary necessary weight gain

Method used

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  • Machine arm quick-release structure for multi-rotor unmanned aerial vehicle
  • Machine arm quick-release structure for multi-rotor unmanned aerial vehicle
  • Machine arm quick-release structure for multi-rotor unmanned aerial vehicle

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Embodiment

[0029] Such as figure 1 with figure 2 As shown, a multi-rotor UAV with a quick-release arm structure is divided into two parts, wherein the lock 1, the support plate 2, the lock guide rail 21, the fulcrum A3, the fuselage socket plate 4, and the fulcrum B5 are installed on the fuselage On the center plate, the center plate of the fuselage needs to design the corresponding positions according to the installation holes of the fulcrum A3 and the fulcrum B5. The fulcrum A3 and the fulcrum B5 are sequentially provided with round holes coaxial with the center line, and are connected with the support plate 2 by screws; The inner liner 6, the arm socket plate 7, the arm limiter 9, and the sleeve 10 are installed on the arm 8. The arm 8 needs to use carbon tubes with a diameter of 25mm, and the position needs to be reserved according to the installation hole of the arm inner liner 6. , and is fixedly connected with the machine arm lining 6, the machine arm 8 is covered with the machi...

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Abstract

The invention discloses a machine arm quick-release structure for a multi-rotor unmanned aerial vehicle, which comprises a locking fastener, a locking fastener guide rail, a fulcrum A, a fuselage socket board, a fulcrum B, an arm lining, an arm socket board, an arm, an arm limit position and a sleeve; the arm quick-release structure comprises a locking fastener, a locking fastener guide rail, a fulcrum A, a fuselage socket board, a fulcrum B, an arm lining, an arm socket board, an arm limit position and a sleeve. The locking fastener, the locking fastener guide rail, the fulcrum A, the fuselage socket board and the fulcrum B are arranged on the fuselage center board, and the fuselage center board is provided with screw holes for installing the fulcrum A and the fulcrum B; The machine arm inner liner, the machine arm socket board, the machine arm limit position and the sleeve are installed on the machine arm; 25 mm diameter carbon pipe are arranged on that arm, and are fixedly connectewith the inner liner of the arm; The upper arm of the machine is provided with an organic arm limit, and the arm limit is connected with the fulcrum B through a sleeve. The arm quick dismantling structure has integral quick dismantling capability, greatly reduces the storage volume required by the multi-rotor unmanned aerial vehicle, is convenient to carry and transport, simultaneously guaranteesthe deployment speed, does not need to use the tool to assist the installation, and has simple structure and convenient maintenance.

Description

technical field [0001] The invention relates to the field of multi-rotor UAVs, in particular to a quick-dismantling structure for arms of multi-rotor UAVs. Background technique [0002] Common aircraft are divided into fixed-wing, helicopter and multi-rotor (four-rotor is the most mainstream). In recent years, due to its excellent control performance, multi-rotor has quickly become a new star in the field of aerial photography and model aircraft sports. At present, multi-rotors have become the mainstream of micro drones or model aircraft. Since UAVs need to be transported by small vehicles, in order to facilitate transportation, micro UAVs with a wheelbase of about 1m have become the mainstream trend in the industry. Among the existing miniature multi-rotor UAVs, when the wheelbase reaches about 1m, for the convenience of accommodation, the folding arm is often the first choice for this type of model, and there are also some cases where the arm and the frame are directly co...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/08B64C1/00
CPCB64C1/069B64C27/08B64U10/10
Inventor 杨扬顾圣骏
Owner SHANGHAI BOONRAY INTELLIGENT TECH CO LTD
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