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Rib integral wall plate damage tolerance optimization method

A technology of integral siding and damage tolerance, applied in design optimization/simulation, special data processing applications, instruments, etc., can solve problems such as lack of processes and methods

Inactive Publication Date: 2021-04-30
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a method for optimizing the damage tolerance of the overall wall panel with ribs, which solves the problem of lack of processes and methods in the optimization design of the overall wall panel, so as to maximize the damage tolerance performance of the overall panel and ensure that the aircraft safe to use

Method used

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  • Rib integral wall plate damage tolerance optimization method
  • Rib integral wall plate damage tolerance optimization method
  • Rib integral wall plate damage tolerance optimization method

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Embodiment Construction

[0035] The embodiment of the present invention provides a method for optimizing the damage tolerance of the integral wall panel with ribs, such as figure 1 shown, including the following steps:

[0036] S1, determine multiple groups of parameters to be optimized for the overall wall panel of ribs, and form an optimization matrix;

[0037] S2. Select a set of rib parameters in the optimization matrix;

[0038] S3, establish a finite element model of the overall wall plate containing at least two ribs, and assume a penetrating crack with an initial length a at the center skin;

[0039] S4, expanding the penetrating crack in the finite element model, and calculating the crack growth life under the set of rib parameters;

[0040] S5. Comparing the crack propagation life under different rib parameters, selecting the rib parameter with the largest crack growth life as the optimal result, and the damage tolerance performance of the overall wall plate is the best under the optimal r...

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Abstract

The invention belongs to the field of aircraft structure damage tolerance design, and discloses a rib integral panel damage tolerance optimization method, which comprises the steps of integral panel reinforcement ratio determination, rib sensitive parameter recognition, structure size optimization matrix establishment, crack-containing integral panel finite element model establishment, stress intensity factor k calculation and crack propagation life calculation. And determining optimal structure parameters through comparison of crack propagation lives under different sizes.

Description

technical field [0001] The invention belongs to the field of damage tolerance design of aircraft structures, and in particular relates to a method for optimizing the damage tolerance of rib overall wall plates. Background technique [0002] Due to the advantages of good fatigue performance, simple manufacture and light structure weight, the integral panel has been applied in many medium and large aircraft structures. However, compared with the traditional riveted siding, the integral siding lacks the natural crack arresting element—the rivet connecting the stringer and the skin, which makes the damage tolerance performance poor. The damage tolerance characteristics of the panels are an important design point for integral panels used in aircraft structures. In the past few years, when the structural design of the integral wall panel generally focused on the static strength performance, if the requirements were met, only a passive check was performed on whether the wall panel...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/23G06F113/28G06F119/14
CPCG06F30/15G06F30/23G06F2113/28G06F2119/14Y02T90/00
Inventor 秦剑波彭航周颜赵天娇
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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