Residual strength prediction for aircraft panels with multiple site damage (MSD) using the elastic plastic finite element alternating method (EPFEAM)

C. R. Pyo; H. Okada; L. Wang; F. W. Brust; S. N. Atluri

Residual strength prediction for aircraft panels with multiple site damage (MSD) using the elastic plastic finite element alternating method (EPFEAM)

C. R. Pyo, H. Okada, L. Wang, F. W. Brust, S. N. Atluri

Mechanical Engineering

Research output: Contribution to journal › Conference article › peer-review

1 Scopus citations

Abstract

A new analytical method for solving stable crack propagation problems is presented for estimating the maximum load carrying capacity of a ductile panel with a row of cracks. The elastic plastic finite element alternating method was extended to account for the propagating cracks. The crack propagation algorithm utilizes the analytic crack solution to release the stress behind the growing crack tip. The T*_ε integral is employed for the crack extension criterion and accounts for the near tip crack growth energy dissipation. A series of analysis have been conducted and the predicted results compare favorably to experimental results.

Original language	English
Pages (from-to)	73-80
Number of pages	8
Journal	American Society of Mechanical Engineers, Aerospace Division (Publication) AD
Volume	47
State	Published - 1995
Event	Proceedings of the 1995 ASME International Mechanical Engineering Congress and Exposition - San Francisco, CA, USA Duration: Nov 12 1995 → Nov 17 1995

Cite this

@article{c07ff05edf544d62b3fa572ebc54e17e,

title = "Residual strength prediction for aircraft panels with multiple site damage (MSD) using the elastic plastic finite element alternating method (EPFEAM)",

abstract = "A new analytical method for solving stable crack propagation problems is presented for estimating the maximum load carrying capacity of a ductile panel with a row of cracks. The elastic plastic finite element alternating method was extended to account for the propagating cracks. The crack propagation algorithm utilizes the analytic crack solution to release the stress behind the growing crack tip. The T*ε integral is employed for the crack extension criterion and accounts for the near tip crack growth energy dissipation. A series of analysis have been conducted and the predicted results compare favorably to experimental results.",

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year = "1995",

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journal = "American Society of Mechanical Engineers, Aerospace Division (Publication) AD",

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note = "null ; Conference date: 12-11-1995 Through 17-11-1995",

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Residual strength prediction for aircraft panels with multiple site damage (MSD) using the elastic plastic finite element alternating method (EPFEAM). / Pyo, C. R.; Okada, H.; Wang, L. et al.

In: American Society of Mechanical Engineers, Aerospace Division (Publication) AD, Vol. 47, 1995, p. 73-80.

Research output: Contribution to journal › Conference article › peer-review

TY - JOUR

T1 - Residual strength prediction for aircraft panels with multiple site damage (MSD) using the elastic plastic finite element alternating method (EPFEAM)

AU - Pyo, C. R.

AU - Okada, H.

AU - Wang, L.

AU - Brust, F. W.

AU - Atluri, S. N.

PY - 1995

Y1 - 1995

N2 - A new analytical method for solving stable crack propagation problems is presented for estimating the maximum load carrying capacity of a ductile panel with a row of cracks. The elastic plastic finite element alternating method was extended to account for the propagating cracks. The crack propagation algorithm utilizes the analytic crack solution to release the stress behind the growing crack tip. The T*ε integral is employed for the crack extension criterion and accounts for the near tip crack growth energy dissipation. A series of analysis have been conducted and the predicted results compare favorably to experimental results.

AB - A new analytical method for solving stable crack propagation problems is presented for estimating the maximum load carrying capacity of a ductile panel with a row of cracks. The elastic plastic finite element alternating method was extended to account for the propagating cracks. The crack propagation algorithm utilizes the analytic crack solution to release the stress behind the growing crack tip. The T*ε integral is employed for the crack extension criterion and accounts for the near tip crack growth energy dissipation. A series of analysis have been conducted and the predicted results compare favorably to experimental results.

UR - http://www.scopus.com/inward/record.url?scp=0029422998&partnerID=8YFLogxK

M3 - Conference article

AN - SCOPUS:0029422998

SN - 0733-4230

VL - 47

SP - 73

EP - 80

JO - American Society of Mechanical Engineers, Aerospace Division (Publication) AD

JF - American Society of Mechanical Engineers, Aerospace Division (Publication) AD

Y2 - 12 November 1995 through 17 November 1995

ER -

Residual strength prediction for aircraft panels with multiple site damage (MSD) using the elastic plastic finite element alternating method (EPFEAM)

Abstract

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