CN113343529A8 - Global control method and device for damage and fracture of integral wallboard structure - Google Patents

Global control method and device for damage and fracture of integral wallboard structure Download PDF

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Publication number
CN113343529A8
CN113343529A8 CN202110657161.8A CN202110657161A CN113343529A8 CN 113343529 A8 CN113343529 A8 CN 113343529A8 CN 202110657161 A CN202110657161 A CN 202110657161A CN 113343529 A8 CN113343529 A8 CN 113343529A8
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China
Prior art keywords
damage
parameters
crack propagation
group
fracture
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CN202110657161.8A
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Chinese (zh)
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CN113343529A (en
CN113343529B (en
Inventor
庄茁
宁宇
张志楠
王恒
柳占立
秦剑波
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Aviation Army Institute People's Liberation Army Air Force Research Institute
First Aircraft Design And Research Institute Of Aviation Industry
Tsinghua University
Original Assignee
Aviation Army Institute People's Liberation Army Air Force Research Institute
First Aircraft Design And Research Institute Of Aviation Industry
Tsinghua University
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Application filed by Aviation Army Institute People's Liberation Army Air Force Research Institute, First Aircraft Design And Research Institute Of Aviation Industry, Tsinghua University filed Critical Aviation Army Institute People's Liberation Army Air Force Research Institute
Priority to CN202110657161.8A priority Critical patent/CN113343529B/en
Publication of CN113343529A publication Critical patent/CN113343529A/en
Publication of CN113343529A8 publication Critical patent/CN113343529A8/en
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
    • G06T17/00—Three dimensional [3D] modelling, e.g. data description of 3D objects
    • G06T17/20—Finite element generation, e.g. wire-frame surface description, tesselation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/04—Ageing analysis or optimisation against ageing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Theoretical Computer Science (AREA)
  • Geometry (AREA)
  • General Physics & Mathematics (AREA)
  • Computer Hardware Design (AREA)
  • Evolutionary Computation (AREA)
  • General Engineering & Computer Science (AREA)
  • Computer Graphics (AREA)
  • Software Systems (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

The invention discloses a global control method and a device for damage and fracture of an integral wallboard structure, and relates to the field of design of damage tolerance of an aircraft structure, wherein the method comprises the following steps: establishing a global damage parameter matrix of the whole wallboard structure; determining a control constraint; selecting a first group of parameters, and establishing a three-dimensional shell finite element model of an integral wall plate structure at least comprising three ribs according to the first group of parameters; simulating a crack propagation track by using a finite element method based on the reinforced area and the reinforced unit, and acquiring a change curve of the stress intensity factor along with the crack length; calculating the crack propagation life, the residual strength value and the weight under the first group of parameters according to the change curve; judging whether the crack propagation life, the residual strength value and the weight meet preset conditions or not; if any one of the conditions does not meet the preset condition, returning to the step: a second set of parameters is selected. The invention can maximally delay the crack propagation speed, improve the damage tolerance performance of the whole wallboard and ensure the quick iteration of the optimized design.
CN202110657161.8A 2021-06-11 2021-06-11 Global control method and device for damage and fracture of integral wallboard structure Active CN113343529B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202110657161.8A CN113343529B (en) 2021-06-11 2021-06-11 Global control method and device for damage and fracture of integral wallboard structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202110657161.8A CN113343529B (en) 2021-06-11 2021-06-11 Global control method and device for damage and fracture of integral wallboard structure

Publications (3)

Publication Number Publication Date
CN113343529A CN113343529A (en) 2021-09-03
CN113343529A8 true CN113343529A8 (en) 2021-11-26
CN113343529B CN113343529B (en) 2022-07-12

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN202110657161.8A Active CN113343529B (en) 2021-06-11 2021-06-11 Global control method and device for damage and fracture of integral wallboard structure

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CN (1) CN113343529B (en)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101561365A (en) * 2009-06-04 2009-10-21 中国航空工业集团公司西安飞机设计研究所 Damage-tolerance testing method for whole wing spar of airplane
FR3052891B1 (en) * 2016-06-20 2018-06-15 Safran Aircraft Engines METHOD OF ESTIMATING THE STRESS INTENSITY FACTOR AND METHOD OF CALCULATING THE LIFETIME OF THE ASSOCIATED
CN106354934B (en) * 2016-08-30 2019-07-02 中航沈飞民用飞机有限责任公司 A kind of Material Stiffened Panel Damage Tolerance Analysis method solved based on finite element analysis
CN111046610B (en) * 2019-12-26 2023-05-23 中国航空工业集团公司西安飞机设计研究所 Calculation method of dimensionless stress intensity factor of integral wing spar of airplane
CN112417606B (en) * 2020-12-08 2023-12-05 江苏科技大学 Calculation method for fatigue life of three-dimensional crack propagation on spherical shell surface
CN112733262A (en) * 2020-12-29 2021-04-30 中国航空工业集团公司西安飞机设计研究所 Rib integral wall panel damage tolerance optimization method

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CN113343529A (en) 2021-09-03
CN113343529B (en) 2022-07-12

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Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
CI02 Correction of invention patent application

Correction item: Applicant|Address|Applicant

Correct: Tsinghua University|100084 Tsinghua University, Beijing, Haidian District|First aircraft design and Research Institute of aviation industry|Air Force Research Institute of the Air Force Research Institute of the Chinese people's Liberation Army

False: Tsinghua University|100084 Tsinghua University, Beijing, Haidian District|First aircraft design and Research Institute of aviation industry|Air Force Research Institute of the Air Force Research Institute of the Chinese people's Liberation Army

Number: 36-02

Page: The title page

Volume: 37

Correction item: Applicant|Address|Applicant

Correct: Tsinghua University|100084 Tsinghua University, Beijing, Haidian District|First aircraft design and Research Institute of aviation industry|Air Force Research Institute of the Air Force Research Institute of the Chinese people's Liberation Army

False: Tsinghua University|100084 Tsinghua University, Beijing, Haidian District|First aircraft design and Research Institute of aviation industry|Air Force Research Institute of the Air Force Research Institute of the Chinese people's Liberation Army

Number: 36-02

Volume: 37

CI02 Correction of invention patent application
GR01 Patent grant
GR01 Patent grant