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Externally-mounted transition beam of airplane wing

A technology of transition beams and wings, which is applied to wings, aircraft parts, transportation and packaging, etc. It can solve the problems of small number of mounted equipment, difficulty in meeting special requirements of aircraft due to the influence of aircraft resistance, and large volume.

Inactive Publication Date: 2017-09-12
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] Since the wing structure is an important component that provides lift to the aircraft and is also an important load-bearing component of the aircraft structure, the traditional wing transition beam adopts the method of sheet metal assembly, and the number of mounted equipment is small and the volume is large, and the The influence of aircraft drag, etc. has been difficult to meet some special requirements of the aircraft

Method used

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  • Externally-mounted transition beam of airplane wing
  • Externally-mounted transition beam of airplane wing
  • Externally-mounted transition beam of airplane wing

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Embodiment Construction

[0033] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention discloses an external wing transition beam, which belongs to the technical field of aircraft structure design. It includes a vertical transition beam (1) and two horizontal transition beams (2), one end of the vertical transition beam (1) is fixed at the lower wall plate of the wing, and the two horizontal transition beams (2) are symmetrically distributed on At the other end of the vertical transition beam (1), grooves are arranged on the horizontal transition beam, and the cross section of the vertical transition beam (1) is streamlined. The external wing transition beam structure of the invention can meet the requirements of the mounted equipment, and the structural strength meets the design requirements, and at the same time, it will not affect the lift and drag of the aircraft.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure design, and in particular relates to an external wing transition beam. Background technique [0002] In the current aircraft development, according to the modification requirements of the aircraft, it is necessary to mount a certain amount of equipment and instruments on the lower part of the wing. For this reason, it is necessary to design a transition beam structure at the lower part of the wing for mounting equipment and instruments. According to the functions and requirements of the aircraft and combined with the characteristics of the aircraft itself, the structural design of the transition beam needs to meet the following five conditions: [0003] 1) The external transition beam structure can meet the requirements of the mounted equipment; [0004] 2) The external transition beam structure will not affect the lift and drag of the aircraft; [0005] 3) The external transition be...

Claims

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Application Information

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IPC IPC(8): B64C3/00B64D47/00
CPCB64C3/00B64D47/00
Inventor 钱利民吴红锋陈栋梁苗志敏魏敏楠
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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