Paper Title:
Global-Local Hierarchical Analysis Techniques for Damaged Aircraft Fuselage Considering Bulging Deformation of Crack
  Abstract

In order to calculate the fracture parameters (Stress intensity factor) in a complicated 3- dimention aircraft model with damage in the aircraft panel, a new two steps global-local hierarchical analysis strategy is used. This paper primarily describes the development and application of advanced computational analysis techniques to determine stress intensity factors for the damaged panels based on the two steps hierarchical analysis strategy from global to 3-D local model, the bulging deformation of crack can be considered in the local model. A fracture parameter calculation programme based on automated global-local procedure to simulate cracked aircraft panel tests is developed for the hierarchical strategy. This programme may create models of two stages, transfer boundary conditions, calculate and obtain fracture parameter automatically. Finally, this paper presents some of the experimental data and the calculated fracture parameters are compared with the experimental results.

  Info
Periodical
Key Engineering Materials (Volumes 324-325)
Edited by
M.H. Aliabadi, Qingfen Li, Li Li and F.-G. Buchholz
Pages
871-874
DOI
10.4028/www.scientific.net/KEM.324-325.871
Citation
J. S. Ju, X. G. Jiang, X. R. Fu, "Global-Local Hierarchical Analysis Techniques for Damaged Aircraft Fuselage Considering Bulging Deformation of Crack", Key Engineering Materials, Vols. 324-325, pp. 871-874, 2006
Online since
November 2006
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$32.00
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