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Unmanned aerial vehicle body cabin section

A technology for drones and fuselages, applied in the direction of fuselage bulkheads, fuselages, fuselage frames, etc., can solve problems that do not meet the requirements of drone weight reduction

Pending Publication Date: 2021-03-12
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, in order to meet the load-carrying requirements, the fuselage compartments of multi-design UAVs have a relatively large mass, which does not meet the current requirements for weight reduction of UAVs.

Method used

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  • Unmanned aerial vehicle body cabin section
  • Unmanned aerial vehicle body cabin section
  • Unmanned aerial vehicle body cabin section

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Embodiment Construction

[0051] In order to make the technical solution of the present application and its advantages clearer, the technical solution of the present application will be further clearly and completely described in detail below in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only part of the application Examples are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the drawings, and other relevant parts can refer to the general design. In the case of no conflict, the embodiments in the application and the technologies in the embodiments Features can be combined with each other to obtain new embodiments.

[0052] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the application shall have the usual meanings und...

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Abstract

The invention belongs to the technical field of unmanned aerial vehicle body cabin section design, and particularly relates to an unmanned aerial vehicle body cabin section which comprises a front ring frame, a middle ring frame and a rear ring frame which are sequentially arranged, a honeycomb bottom plate, a grid wall plate, and a honeycomb skin; the honeycomb bottom plate is arranged between the front ring frame and the middle ring frame, one end of the honeycomb bottom plate is connected with the front ring frame, and the other end of the honeycomb bottom plate is connected with the middlering frame; the grid wall plate is arranged between the middle ring frame and the rear ring frame, one end of the grid wall plate is connected with the middle ring frame, and the other end is connected with the rear ring frame; one side edge of the honeycomb skin is connected with one side edge of the honeycomb bottom plate and one side edge of the grid wall plate, and the other side edge of thehoneycomb skin is connected with the other side edge of the honeycomb bottom plate and the other side edge of the grid wall plate, and the honeycomb skin covers the front annular frame, the middle annular frame and the rear annular frame.

Description

technical field [0001] The application belongs to the technical field of UAV fuselage section design, and in particular relates to a UAV fuselage section. Background technique [0002] The fuselage section of the drone bears surface pressure loads during the flight of the drone and is connected to the landing gear. During the take-off and landing of the drone, it bears the impact load transmitted by the landing gear, which is an important load on the drone. structure. [0003] At present, in order to meet the load-carrying needs, the fuselage compartments of multi-design UAVs have a relatively large mass, which does not meet the current requirements for weight reduction of UAVs. [0004] In view of the existence of above-mentioned technical defect, propose this application. [0005] It should be noted that the disclosure of the above background technical content is only used to assist in understanding the inventive concepts and technical solutions of the present invention,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/06B64C1/10B64C1/12B64C1/14
CPCB64C1/061B64C1/10B64C1/12B64C1/1407
Inventor 许阳阳苏亚东金凤新赵博王德刚陈召斌李宪开季宝峰王志勇刘含洋
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA