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Cantilever of electric unmanned aerial vehicle

An electric unmanned aerial vehicle and cantilever technology, applied in the field of unmanned aerial vehicles, can solve the problems of unreasonable strength distribution and large structural weight, and achieve the effects of light weight, excellent weight reduction effect, and large torsional performance.

Pending Publication Date: 2018-01-19
沈阳旋飞航空技术有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The cantilever of the unmanned aerial vehicle of this prior art also adopts the solid bar of equal diameter, and the intensity distribution is unreasonable, and the structural weight is also big

Method used

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  • Cantilever of electric unmanned aerial vehicle
  • Cantilever of electric unmanned aerial vehicle
  • Cantilever of electric unmanned aerial vehicle

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Embodiment Construction

[0023] In order to have a clearer understanding of the technical features, purposes and effects of the present invention, the specific implementation manners of the present invention will now be described with reference to the accompanying drawings. Wherein, the same parts adopt the same reference numerals.

[0024] The existing multi-axis UAVs mentioned in the background technology section all adopt a fully symmetrical layout, resulting in the concentration of the center of gravity at one point, and the load layout is greatly restricted. All of them are blocked, so that the carried load cannot launch weapons or observe obliquely upwards, which limits the application range of existing drones. Based on this, the application provides an electric drone, such as figure 1 and 2 As shown, among them, figure 1 Shown is a schematic diagram of the three-dimensional structure of an electric drone according to a specific embodiment of the present invention; figure 2 to show figure ...

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Abstract

The invention provides a cantilever of an electric unmanned aerial vehicle. The cantilever of the electric unmanned aerial vehicle is used for being connected to a vehicle body of the electric unmanned aerial vehicle to support a motor, and the cantilever comprises a first end part connected with the vehicle body, a second end part supporting the motor and a middle section located between the first end part and the second end part. The first end part is composed of a cylinder with the diameter being the same in the length direction. The second end part is composed of a cylinder with the diameter being the same in the length direction as well. The middle section is of a tapered cylindrical structure. The cantilever of the electric unmanned aerial vehicle is integrally of a hollow cylindrical structure, is lower in weight under the same strength situation, and can obtain a larger torsional property. The two ends of the cantilever are designed to be the cylinders with the diameters beingthe same so that cylindrical connection structures can be conveniently inserted in and firm connection can be achieved. The middle section is designed to be of the tapered cylindrical structure, thusequal strength design can be formed, and the lightening effect is better.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a multi-rotor electric unmanned aerial vehicle, in particular to a cantilever of an electric unmanned aerial vehicle. Background technique [0002] With the development of the global general aviation industry, the development of various rotorcraft is also increasing day by day, especially the rotor electric unmanned aircraft, which are widely used in agricultural plant protection, forest fire monitoring, aerial photography, land survey, post-disaster loss assessment tasks. Electric unmanned aerial vehicles have the advantages of simple structure, low noise, flexible maneuverability, quick response, and low operation requirements, and have a large market share in the consumer market. However, the power of electric drones is provided by batteries. The weight of batteries cannot be consumed like fuel, resulting in very limited payloads and short cruise times. They ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/06B64C1/30
Inventor 孙卫华庞振岳刘新民张建飞鲁明宗宁
Owner 沈阳旋飞航空技术有限公司
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