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Method for designing large-span open-section cabin space truss structure

A space truss and structural design technology, applied in design optimization/simulation, special data processing applications, instruments, etc., can solve problems such as complex force transmission paths, large weight costs, and complex connection forms

Pending Publication Date: 2021-04-23
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

However, compared with the closed-section structure, the open-section structure usually has weaker torsional stiffness, and the ability to withstand torque load is very weak. When the structure is subjected to torque load, it is easy to produce large deformation and then damage
[0003] At present, the large-span open-section cabin often uses beam + reinforced frame structure or plate rod structure, but these configurations often have complicated force transmission paths and connection forms, and will bring a large weight cost

Method used

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  • Method for designing large-span open-section cabin space truss structure
  • Method for designing large-span open-section cabin space truss structure
  • Method for designing large-span open-section cabin space truss structure

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Embodiment Construction

[0024] The present invention will be described in detail below.

[0025] It is known that the torque load is 1,000kN*m, the structural material is aluminum alloy (elastic modulus 71000MPa), the stress is controlled within 400MPa, and the relative deformation of two points on the opening edge of the space truss structure section does not exceed 40mm. In this embodiment, a method for designing a space truss structure of a large-span open-section cabin is provided, which specifically includes the following contents:

[0026] step 1: figure 1 is the force analysis diagram of the actual space truss structure, combined with figure 1 As shown, according to the actual space truss structure load situation, the load is decomposed and simplified, and it is determined that the space truss structure bears the transverse shear couple and the vertical shear couple; The ability of the shear couple is strong, but the ability to withstand the transverse shear couple is weak. By designing the ...

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Abstract

The invention belongs to the field of space truss structure arrangement and design of aviation large-span open-section cabin structures under the action of end face torque loads, and particularly relates to an arrangement and optimization design method of a space truss structure during end face torque load transmission. The method comprises the following steps: firstly, designing a force transmission path for the structure on the basis of theoretical analysis; then establishing a finite element model of the space truss structure, and applying load and displacement boundary conditions; secondly, taking the minimum weight as an optimization target, giving constraint conditions of stress strain and displacement, and achieving redistribution of loads by changing the rigidity of spring elements; and performing multiple rounds of iterative optimization on the space truss structure to obtain a final optimization result.

Description

technical field [0001] The invention belongs to the field of arrangement and design of a space truss structure under the action of an end face torque load of an aviation large-span open-section cabin structure, and in particular relates to an arrangement and an optimal design method of a space truss structure when transmitting end face torque loads. Background technique [0002] Large-span open-section cabin structures are widely used in aircraft, and due to the complexity of the aircraft's stress environment, open-section cabin structures often bear torque loads. However, compared with the closed-section structure, the open-section structure usually has weaker torsional stiffness, and the ability to bear torque load is very weak. When the structure is subjected to torque load, it is easy to produce large deformation and then fail. [0003] At present, the large-span open-section cabin often uses a beam + reinforced frame structure or a plate rod structure, but these configu...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/23G06F119/14
CPCG06F30/15G06F30/23G06F2119/14
Inventor 崔勇江李鹏飞柴慧
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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