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Fuselage assembly for unmanned aerial vehicle and unmanned aerial vehicle with fuselage assembly

A technology for unmanned aerial vehicles and fuselages, applied in the direction of fuselage, aircraft parts, fuselage frame, etc., can solve the problems of the structure of the fuselage components that need to be improved, the structural strength of the connecting beam is low, and the structure of the connecting beam is heavy, etc., so as to reduce the weight , Improve production efficiency, improve the effect of structural strength

Pending Publication Date: 2021-02-09
GUANGZHOU XAIRCRAFT TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] In the fuselage assembly of the UAV in the related art, the structural strength of the connecting beam used to connect the mounting frame and the machine arm is low, the assembly time is long, and there are many connecting parts (such as screws, pins, etc.) required for assembly. As a result, the connecting beam structure is relatively heavy, and the structure of the fuselage components needs to be improved

Method used

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  • Fuselage assembly for unmanned aerial vehicle and unmanned aerial vehicle with fuselage assembly
  • Fuselage assembly for unmanned aerial vehicle and unmanned aerial vehicle with fuselage assembly
  • Fuselage assembly for unmanned aerial vehicle and unmanned aerial vehicle with fuselage assembly

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Embodiment Construction

[0105] Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary only for explaining the present invention and should not be construed as limiting the present invention.

[0106] In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", " Back", "Left", "Right", "Vertical", "Horizontal", "Top", "Bottom", "Inner", "Outer", "Clockwise", "Counterclockwise", "Axial" , "radial", "circumferential" and other indicated orientations or positional relationships are based on the orientations or positional relationships shown in the drawings, which are only for the convenience of describing the present ...

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Abstract

The invention discloses a fuselage assembly for an unmanned aerial vehicle and the unmanned aerial vehicle with the fuselage assembly. The fuselage assembly comprises a mounting frame; a connecting beam which is fixedly connected with the mounting frame, and the connecting beam is an integrally formed part; and the plurality of vehicle arms which are arranged on the connecting beam at intervals. According to the fuselage assembly, the production efficiency of the connecting beam is high, the structural strength is high, and the assembly efficiency of the fuselage assembly can be effectively improved. And the weight of the connecting beam can be reduced to a certain extent, so that the fuselage assembly is light.

Description

technical field [0001] The invention relates to the technical field of drones, in particular to a fuselage assembly for drones and a drone with the same. Background technique [0002] In the fuselage assembly of the UAV in the related art, the structural strength of the connecting beam used to connect the mounting frame and the machine arm is low, the assembly time is long, and there are many connecting parts (such as screws, pins, etc.) required for assembly. Furthermore, the connecting beam structure is relatively heavy, and the structure of the fuselage components needs to be improved. Contents of the invention [0003] The present invention aims to solve at least one of the technical problems existing in the prior art. Therefore, an object of the present invention is to provide a fuselage assembly for a drone, which has high production efficiency and high structural strength of the connecting beam, and can effectively improve the assembly efficiency of the fuselage as...

Claims

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Application Information

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IPC IPC(8): B64C1/06B64C1/00
CPCB64C1/00B64C1/064B64C1/068Y02T50/40
Inventor 徐智芹何建兵肖锭锋
Owner GUANGZHOU XAIRCRAFT TECH CO LTD
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