scholarly journals Dynamic fracture analysis technique of aircraft fuselage containing damage subjected to blast

2013 ◽  
Vol 58 (3-4) ◽  
pp. 627-633 ◽  
Author(s):  
Jinsan Ju ◽  
Xiaochuan You
Keyword(s):  
Dynamic Fracture ◽  
Fracture Analysis ◽  
Aircraft Fuselage ◽  
Analysis Technique

Fracture Analysis for Stiffened Aircraft Fuselage Using Substructure Method

2008 ◽  
Vol 385-387 ◽  
pp. 837-840
Author(s):  
Jin San Ju ◽  
Xiu Gen Jiang ◽  
Xiang Rong Fu
Keyword(s):  
Computational Analysis ◽  
Fracture Analysis ◽  
Fracture Parameter ◽  
Intensity Factors ◽  
Analysis Techniques ◽  
Aircraft Fuselage ◽  
Analysis Technique ◽  
Substructure Analysis ◽  
Global And Local ◽  
Aircraft Panels

This paper primarily describes the development and application of substructure computational analysis techniques in two-step hirarchical strategy to determine stress intensity factors for the stiffened damaged panels subjected to fatigue internal pressure. A program based on substructure analysis technique and global-local hierarchical strategy has been developed for the fracture analysis of curved aircraft panels containing cracks. This program may create superelements in global and local models, and obtain fracture parameter of the crack in local model by expanding results in superelements automatically. The technique is applied to the analysis of a cracked panel with 7 frames and 10 stringers. SIFs of four cracks in it with different crack lengths are obtained efficiently.

Fracture Analysis for Damaged Aircraft Fuselage Using Substructure Method

2008 ◽  
Vol 33-37 ◽  
pp. 29-34
Author(s):  
Jin San Ju ◽  
Xiao Chuan You ◽  
Xiu Gen Jiang ◽  
Jin Zhao Zhuang
Keyword(s):  
Longitudinal Crack ◽  
Numerical Approach ◽  
Fracture Analysis ◽  
Fracture Parameter ◽  
Aircraft Fuselage ◽  
Panel Model ◽  
Analysis Technique ◽  
Curved Panel ◽  
Substructure Analysis ◽  
Typical Test

This paper primarily describes the development and application of substructure computational analysis techniques to determine stress intensity factors for the damaged panels subjected to fatigue internal pressure. A program based on substructure analysis technique has been developed for the fracture analysis of curved aircraft panels containing cracks. This program may create whole model which consists of substructure superelements and obtain fracture parameter of the crack by expanding results in superelement automatically. For instance, a typical test curved panel model consists of 7 frames and 8 stringers is calculated. This numerical approach has been validated through comparison between the calculation SIF results and available experimental data of a typical test panel with a longitudinal crack. The technique that has been established here is also applied to the other analysis of a test series of cracked panel with 7 frames and 10 stringers. SIFs of four cracks in it with different crack lengths are obtained efficiently.

Dynamic fracture analysis of a stiffened panel with an edge crack

1993 ◽  
Vol 46 (2) ◽  
pp. 329-338
Author(s):  
Yuanhan Wang ◽  
Zaihua Liu ◽  
Jian Wang
Keyword(s):  
Dynamic Fracture ◽  
Edge Crack ◽  
Fracture Analysis ◽  
Stiffened Panel

Dynamic Fracture Analysis of Aluminum Honeycomb Sandwich Panel

2006 ◽  
pp. 67-72
Author(s):  
Byung Il Kim ◽  
Byeong Wook Noh ◽  
Young Woo Choi ◽  
Sung In Bae ◽  
Jung Il Song
Keyword(s):  
Dynamic Fracture ◽  
Sandwich Panel ◽  
Fracture Analysis ◽  
Honeycomb Sandwich ◽  
Aluminum Honeycomb

FEM Dynamic Fracture Analysis OF Concrete Beams

1989 ◽  
Vol 115 (10) ◽  
pp. 2136-2149 ◽  
Author(s):  
Jiaji Du ◽  
Albert S. Kobayashi ◽  
Neil M. Hawkins
Keyword(s):  
Dynamic Fracture ◽  
Concrete Beams ◽  
Fracture Analysis
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