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Structural hierarchy type finite element simulation analysis method under complex load condition

A complex load and simulation analysis technology, applied in design optimization/simulation, special data processing applications, instruments, etc., can solve the problems of partial model analysis coverage and accuracy reduction

Active Publication Date: 2017-09-08
SHANGHAI AEROSPACE SYST ENG INST
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

This fragmentation reduces the coverage and accuracy of local model analysis to a certain extent.

Method used

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  • Structural hierarchy type finite element simulation analysis method under complex load condition
  • Structural hierarchy type finite element simulation analysis method under complex load condition
  • Structural hierarchy type finite element simulation analysis method under complex load condition

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Embodiment Construction

[0025] The present invention is described in detail below in conjunction with embodiment, present embodiment implements under the premise of technical scheme of the present invention, has provided detailed implementation, but protection scope of the present invention is not limited to following embodiment.

[0026] Such as figure 1 As shown, it is a schematic diagram of the main structure of a cabin according to an embodiment of the present invention, and the structure bears concentrated loads at the joints.

[0027] The structural hierarchical finite element simulation analysis method under complex load conditions provided by the present invention, in more detail, includes the following steps:

[0028] Step 1: Establish a full-scale finite element model of the cabin structure as the parent model. Such as figure 2 On the right, the skin is simplified as a weakly rigid plate element, and the stringers, frames, and joints are simplified as plate elements; for example figure...

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Abstract

The invention discloses a structural hierarchy type finite element simulation analysis method under complex load conditions; the method comprises the following steps: S1, building a cabin body main structure full-scale finite element model as the first level master model; S2, aiming at a main structure failure mode and carrying out finite element calculation, wherein a calculation method contains structural stability analysis and static force intensity analysis; S3, carrying out danger assessment for a local instability position having a main structure instability load lower than 1.5 times of the designed load, and selecting a refinement analysis area; S4, carrying out danger assessment for a stress danger area having a main structure intensity residue coefficient lower than 1.3, and selecting a refinement analysis area; S5, building a finite element 1st level sub model according to the refinement analysis areas in S3 and S4; S6, building a finite element connecting model between the sub model and the master model; S7, submitting finite element calculation for the sum model having a transition model; S8, repeating S1-S7 until the model is exquisite enough.

Description

technical field [0001] The invention relates to the field of carrier and aircraft strength design, in particular to a numerical analysis method for the main structure strength of a cabin body. Background technique [0002] The current development of spaceflight poses unprecedented challenges to the simulation industry. On the one hand, the lightweight design makes the structural design margin continue to decrease, which puts forward strict requirements for the accuracy of the simulation pre-test. On the other hand, intensive launch and intensive design require continuous improvement of work efficiency, which is implemented in the simulation industry to continuously improve the efficiency of simulation modeling and analysis. For cabin structures with complex loads and complex layouts, the contradiction between the accuracy of the simulation method and the calculation efficiency is more prominent, so it is necessary to study a finite element analysis method that can take both...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23G06F2111/20G06F2119/06
Inventor 冀宾史立涛杨颜志王瑞凤李昊吕榕新张修科
Owner SHANGHAI AEROSPACE SYST ENG INST
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