Life prediction of aerospace structures by combined XFEM and advanced fatigue models

Jim Lua, Jay Shi, Zizi Lu, Yongming Liu

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

An advanced fatigue life prediction for aerospace structures is developed by integration of an extended finite element method (XFEM) for mesh independent crack modeling with a small-scale fatigue model for stress ratio dependent and variable amplitude loading. Different from a traditional cycle-based fatigue analysis approach, the small scale model is implemented based on the incremental crack growth at any time instant during a cycle. The stress ratio effects are included using the forward and reverse plastic zone interaction. The concept of the reversed plastic zone is applied to determine the lower integration limit in a single load cycle. Given an arbitrary fatigue crack growth increment determined from the small scale model, a fast matching and narrow band technique is implemented to provide an efficient way to track a curvilinear crack growth without remeshing. Different from the existing post-fatigue analysis approach, the fatigue life is computed concurrently with the crack growth driving force along its front. A comparative study between the small time scale model and the two-parameter was performed for crack growth and life prediction at various stress ratios. Both the validity and computational efficiency of the developed advanced fatigue life prediction tool were demonstrated via its application to compact specimens.

Original languageEnglish (US)
Title of host publicationCollection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
StatePublished - 2010
Externally publishedYes
Event51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference - Orlando, FL, United States
Duration: Apr 12 2010Apr 15 2010

Other

Other51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
CountryUnited States
CityOrlando, FL
Period4/12/104/15/10

Fingerprint

Fatigue of materials
Crack propagation
Plastics
Computational efficiency
Fatigue crack propagation
Cracks
Finite element method

ASJC Scopus subject areas

  • Civil and Structural Engineering
  • Mechanics of Materials
  • Building and Construction
  • Architecture

Cite this

Lua, J., Shi, J., Lu, Z., & Liu, Y. (2010). Life prediction of aerospace structures by combined XFEM and advanced fatigue models. In Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference [2010-2538]

Life prediction of aerospace structures by combined XFEM and advanced fatigue models. / Lua, Jim; Shi, Jay; Lu, Zizi; Liu, Yongming.

Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 2010. 2010-2538.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Lua, J, Shi, J, Lu, Z & Liu, Y 2010, Life prediction of aerospace structures by combined XFEM and advanced fatigue models. in Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference., 2010-2538, 51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Orlando, FL, United States, 4/12/10.
Lua J, Shi J, Lu Z, Liu Y. Life prediction of aerospace structures by combined XFEM and advanced fatigue models. In Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 2010. 2010-2538
Lua, Jim ; Shi, Jay ; Lu, Zizi ; Liu, Yongming. / Life prediction of aerospace structures by combined XFEM and advanced fatigue models. Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 2010.
@inproceedings{eb3ae51aa8e74f72807ef6cb41eebb31,
title = "Life prediction of aerospace structures by combined XFEM and advanced fatigue models",
abstract = "An advanced fatigue life prediction for aerospace structures is developed by integration of an extended finite element method (XFEM) for mesh independent crack modeling with a small-scale fatigue model for stress ratio dependent and variable amplitude loading. Different from a traditional cycle-based fatigue analysis approach, the small scale model is implemented based on the incremental crack growth at any time instant during a cycle. The stress ratio effects are included using the forward and reverse plastic zone interaction. The concept of the reversed plastic zone is applied to determine the lower integration limit in a single load cycle. Given an arbitrary fatigue crack growth increment determined from the small scale model, a fast matching and narrow band technique is implemented to provide an efficient way to track a curvilinear crack growth without remeshing. Different from the existing post-fatigue analysis approach, the fatigue life is computed concurrently with the crack growth driving force along its front. A comparative study between the small time scale model and the two-parameter was performed for crack growth and life prediction at various stress ratios. Both the validity and computational efficiency of the developed advanced fatigue life prediction tool were demonstrated via its application to compact specimens.",
author = "Jim Lua and Jay Shi and Zizi Lu and Yongming Liu",
year = "2010",
language = "English (US)",
isbn = "9781600867422",
booktitle = "Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference",

}

TY - GEN

T1 - Life prediction of aerospace structures by combined XFEM and advanced fatigue models

AU - Lua, Jim

AU - Shi, Jay

AU - Lu, Zizi

AU - Liu, Yongming

PY - 2010

Y1 - 2010

N2 - An advanced fatigue life prediction for aerospace structures is developed by integration of an extended finite element method (XFEM) for mesh independent crack modeling with a small-scale fatigue model for stress ratio dependent and variable amplitude loading. Different from a traditional cycle-based fatigue analysis approach, the small scale model is implemented based on the incremental crack growth at any time instant during a cycle. The stress ratio effects are included using the forward and reverse plastic zone interaction. The concept of the reversed plastic zone is applied to determine the lower integration limit in a single load cycle. Given an arbitrary fatigue crack growth increment determined from the small scale model, a fast matching and narrow band technique is implemented to provide an efficient way to track a curvilinear crack growth without remeshing. Different from the existing post-fatigue analysis approach, the fatigue life is computed concurrently with the crack growth driving force along its front. A comparative study between the small time scale model and the two-parameter was performed for crack growth and life prediction at various stress ratios. Both the validity and computational efficiency of the developed advanced fatigue life prediction tool were demonstrated via its application to compact specimens.

AB - An advanced fatigue life prediction for aerospace structures is developed by integration of an extended finite element method (XFEM) for mesh independent crack modeling with a small-scale fatigue model for stress ratio dependent and variable amplitude loading. Different from a traditional cycle-based fatigue analysis approach, the small scale model is implemented based on the incremental crack growth at any time instant during a cycle. The stress ratio effects are included using the forward and reverse plastic zone interaction. The concept of the reversed plastic zone is applied to determine the lower integration limit in a single load cycle. Given an arbitrary fatigue crack growth increment determined from the small scale model, a fast matching and narrow band technique is implemented to provide an efficient way to track a curvilinear crack growth without remeshing. Different from the existing post-fatigue analysis approach, the fatigue life is computed concurrently with the crack growth driving force along its front. A comparative study between the small time scale model and the two-parameter was performed for crack growth and life prediction at various stress ratios. Both the validity and computational efficiency of the developed advanced fatigue life prediction tool were demonstrated via its application to compact specimens.

UR - http://www.scopus.com/inward/record.url?scp=84855638461&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84855638461&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:84855638461

SN - 9781600867422

BT - Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

ER -