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Method for determining structural parameters of rectangular fuselagelarge-opening structure under torsional load

A technology of torsional load and structural parameters, applied in aircraft parts, special data processing applications, design optimization/simulation, etc., can solve problems such as low efficiency and achieve the effect of improving work efficiency

Active Publication Date: 2021-05-25
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The object of the present invention is to provide a method for determining the structural parameters of the rectangular fuselage large opening structure under torsional load, so as to overcome the dimensional parameter change of the existing finite element calculation method It is necessary to rebuild the model and iteratively calculate the problem of low efficiency

Method used

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  • Method for determining structural parameters of rectangular fuselagelarge-opening structure under torsional load
  • Method for determining structural parameters of rectangular fuselagelarge-opening structure under torsional load
  • Method for determining structural parameters of rectangular fuselagelarge-opening structure under torsional load

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Experimental program
Comparison scheme
Effect test

Embodiment

[0122] For the optimal design of a fuselage cabin structure, the cabin material is 2A12-T4.

[0123] (1) Determine the torsion model

[0124] According to the actual structure, it is simplified to figure 1For the torsional model shown, determine the various dimensional parameters.

[0125] Width b=2440mm, height h=2060mm, opening length L=5000mm, bear torsional load M t =10 9 N mm;

[0126] (2) Determine the allowable stress

[0127] The tensile strength of 2A12-T4 material is σ b =425MPa, considering factors such as nail hole weakening or stress concentration, the allowable value of the structural design of the material can be considered in the design: [σ]=400MPa

[0128] (3) Determine the thickness parameter

[0129] Calculate the thickness according to the steps in the invention scheme as follows:

[0130] According to the stress expression of point A, there are:

[0131]

[0132] According to the stress expression at point B, there are:

[0133]

[0134] Ac...

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Abstract

The invention discloses a method for determining structure parameters of a rectangular fuselage large-opening structure under a torsional load. The method comprises the steps: obtaining a wall thickness determination expression of the type of structure according to a strength control criterion through deep research under the torsional load on the large-opening structure at the lower part of a rectangular section fuselage of an aircraft, and can be used for determining aircraft parameters, and improving the reliability of the aircraft. The aircraft structure design is guided. Compared with a traditional finite element method, when the load, the boundary dimension and the opening dimension change, a finite element model needs to be rebuilt, grids need to be redivided, optimization calculation needs to be loaded, the calculation iteration process is long, and the workload is large. By adopting the formulation parameter determination method obtained by the invention, no matter how the size parameters change, the design parameters of the structure can be quickly obtained, and the working efficiency is greatly improved.

Description

technical field [0001] The invention relates to the field of aeronautical structure design, and in particular proposes a method for determining structural parameters of a rectangular thin-wall fuselage with large openings under torsional load, which can guide the structural design and obtain the optimal solution of the structural design. Background technique [0002] The large opening structure is generally the opening of the lower part of the aircraft fuselage, the installation opening of the cargo hatch, the installation opening of the bomb bay door, etc.; 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 ty...

Claims

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Application Information

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IPC IPC(8): B64F5/00G06F30/23
CPCB64F5/00G06F30/23Y02T90/00
Inventor 苏雁飞赵占文黄烨
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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