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Method for determining vertical rigidity of large-opening structure of rectangular fuselage cabin

A large opening, fuselage technology, applied in the field of determining the vertical stiffness of the large opening structure of the rectangular fuselage cabin, can solve the problems of lack of design technology and experience

Active Publication Date: 2021-05-18
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

However, the technical information on the design of the fuselage's large opening reinforcement is rarely published, resulting in a relative lack of design technology and experience

Method used

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  • Method for determining vertical rigidity of large-opening structure of rectangular fuselage cabin
  • Method for determining vertical rigidity of large-opening structure of rectangular fuselage cabin
  • Method for determining vertical rigidity of large-opening structure of rectangular fuselage cabin

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Embodiment 1

[0115] For a rectangular fuselage section, its width is b=3000mm, its height is h=1500mm, and its wall thickness is δ 0 = 2mm, due to the large opening of the cabin, the lower wall needs to be strengthened by arranging side beams at four corners. When the vertical bending stiffness is consistent with the rigidity of the model without openings, the area F of the side beams to be compensated up with F down How to determine?

[0116] method one:

[0117] 1) From the structure size data,

[0118] When the vertical bending stiffness of the strengthened model is required to be consistent with that of the model before the opening, ξ=1;

[0119] Ruocha F up / F down =2:8 curve, p=1.02 can be obtained.

[0120] Then the areas of the upper and lower side beams are respectively:

[0121]

[0122] Ruocha F up / F down =5:5 curve, available: p=1.10

[0123] Then the areas of the upper and lower side beams are respectively:

[0124]

[0125] Method Two:

[0126] When the v...

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Abstract

The invention belongs to the field of aviation structure design, and particularly relates to a method for determining vertical rigidity of a large-opening structure of a rectangular fuselage cabin. The method comprises the steps of: setting a rigidity ratio of the rectangular fuselage with the large-opening structure to a rectangular fuselage without a large-opening structure, and setting the length, width and wall thickness of a rectangular section of the rectangular fuselage, wherein the two rectangular machine bodies are the same in structure except for the large opening structure; and taking the rigidity ratio and the length, width and height of the rectangular section as parameters, taking the minimum upper boundary beam area and the minimum lower boundary beam area as constraint conditions, and solving an expression of the upper boundary beam area and an expression of the lower boundary beam area.

Description

technical field [0001] The invention belongs to the field of aeronautical structure design, in particular to a method for determining the vertical stiffness of a large opening structure of a rectangular fuselage cabin. Background technique [0002] The large opening structure cuts off the force transmission route of the aircraft structure, which is a difficult point in aircraft design. The conventional large opening of the circular fuselage is based on a small amount of design basis, while the rectangular opening is a special cabin opening, which is a new type of structure. There is a lack of design experience in the model design, and there is no evidence of this type of structure in the aircraft design data. introduce. [0003] In order to minimize the impact of the large opening area on the fuselage and meet the requirements of continuous stiffness and coordinated deformation, the opening area must be strengthened. However, the technical information on the design of the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M5/00
CPCG01M5/00Y02T90/00
Inventor 苏雁飞田晶晶尹凯军赵占文
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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