Evaluation of Crack Arrest Capability in the Stiffened Panel of a Transport Aircraft

The basic fuselage structure is developed primarily based on static strength and stability considerations. The static strength of the bulkhead plays a dominant role in its crack arrest capability. In this investigation, the strength of the rivets and skin in the presence of a longitudinal crack are...

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Bibliographic Details
Published inInternational journal of vehicle structures and systems Vol. 15; no. 6; pp. 769 - 772
Main Authors Arunakumara, P C, Chandregowda, M, Nagesh, S N, Anand, V J
Format Journal Article
LanguageEnglish
Published Chennai MechAero Foundation for Technical Research & Education Excellence 30.12.2023
Subjects
Aircraft
Airframes
Boundary conditions
Bulkheads
Crack arrest
Crack propagation
Fatigue cracks
Fatigue failure
Finite element analysis
Finite element method
Fuselages
Riveted joints
Rivets
Stress analysis
Stress intensity factors
Tensile stress
Transport aircraft
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Summary:The basic fuselage structure is developed primarily based on static strength and stability considerations. The static strength of the bulkhead plays a dominant role in its crack arrest capability. In this investigation, the strength of the rivets and skin in the presence of a longitudinal crack are studied to check the performance of the stiffened panel in arresting the two-bay crack. A finite element analysis approach was used to cany out the parametric study. A stiffened panel with multiple bays was considered for the analysis. The unstrfened fuselage expands uniformly in the radial and longitudinal directions. The fatigue cracks will initiate normally from the highest tensile stress locations. Also, cracks can get initiated due to discrete sources of damage, like tool marks on the surface or pebbles hitting the fuselage. The stress intensity factor (SIP) at deferent crack lengths was calculated. The panel was analysed with a central bulkhead in broken condition.
ISSN:0975-3060
0975-3540
DOI:10.4273/ijvss.15.6.06