Structure of a Modular Deformable UAV

An unmanned aerial vehicle and modular technology, which is applied in the structural field of modular and deformable unmanned aerial vehicles, can solve the problem that the power system cannot meet the high-quality carrying requirements, there is no modular unmanned aerial vehicle product, and the adverse effects of the flight performance of the aircraft are solved. and other problems, to improve the flexibility and redundancy, the connection structure is simple and reliable, and the bolt tightening connection method is reduced.

Active Publication Date: 2022-07-05
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, its mounting form is limited and can only be mounted under the aircraft, which will definitely have an adverse effect on the flight performance of the aircraft
At the same time, the power system it adopts cannot meet the demand for carrying large masses, which limits its application in the express transportation industry
[0006] In short, there is currently no modular drone product that can truly transport goods on the market

Method used

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  • Structure of a Modular Deformable UAV
  • Structure of a Modular Deformable UAV
  • Structure of a Modular Deformable UAV

Examples

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Embodiment Construction

[0037] The present invention will be described in detail below with reference to the accompanying drawings and embodiments.

[0038] The invention provides a structure of a modular and deformable unmanned aerial vehicle, which is assembled by a plurality of single-rotor modules.

[0039] like figure 1 As shown, the single rotor module mainly includes: a cuboid body 1 , a connecting plate 3 , a landing gear 5 , a connecting plate limit rod 6 , a motor seat slide rail 8 and a motor seat 9 .

[0040] The cuboid main body 1 is mainly composed of 1.5mm and 2mm carbon plates. On the premise of satisfying the structural strength, each carbon plate is provided with weight-reducing holes to reduce the mass of the module and achieve the purpose of lightness and simplicity.

[0041] like figure 2As shown, the cuboid body 1 is used to carry the entire device, the interior is hollow, the battery is placed inside, and the lines can be drawn out through the through holes on the side. The...

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Abstract

The invention discloses the structure of a modular deformable unmanned aerial vehicle. The UAV structure of the present invention is composed of a plurality of single-rotor modules spliced ​​together, and the single-rotor module includes: a cuboid body, a connecting plate, a limit rod, a motor seat slide rail and a motor seat; wherein, the cuboid body, the connecting plate, the limiter The rod, the motor seat slide rail and the motor seat are arranged in a "bow" shape, and the deformation of the structure is realized by moving the position of the motor seat. The deformable structure makes it possible to assemble a traditional UAV, or attach to a load to form a special UAV, thus meeting diverse mission requirements and improving the flexibility and redundancy of the UAV . Once a single rotor module is damaged, it can be disassembled and installed, quickly replaced and go-around.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicle structure design, in particular to a structure of a modular and deformable unmanned aerial vehicle. Background technique [0002] The structure of traditional multi-rotor UAVs is mostly integrated with the fuselage, which is large and difficult to carry, has a single function, and is difficult to repair once damaged. [0003] Patent CN205396516U discloses a UAV folding and quick installation structure, including a main wing, a dovetail tenon type turntable, a fuselage, a wing folding part, a main rotating shaft, and a hinge; the upper surface of the dovetail tenon type turntable and the lower surface of the main wing are in the 90° connection, the dovetail tenon type turntable and the fuselage are connected through the main shaft, the middle of the main shaft is provided with a through hole, the main wing is located above the fuselage, the folded part of the wing is above the main ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C37/00B64C27/08
CPCB64C37/00B64C27/08B64U10/10Y02T50/40
Inventor 王佳楠陈昱达兰晓伟严钰巍李杰张瑜
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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