Numerical Study of Cracked Titanium Shell under Compression

Abstract:

Article Preview

In many industrial conditions, light thin titanium shells are well used under various severe loading conditions. It is of interest to know the real conditions that govern the instability of a cracked panel subject to buckling loads in order to conserve as maximum as possible the strength of the structure. Several parameters can be varied in order to achieve this objective. The aim of this study is to determine the evolution of these parameters in order to achieve optimal crack propagation conditions while keeping these parameters within “reasonable” limits of physical and economic feasibility. For the purpose of the current study the considered structure can be regarded as thin cylindrical shell of radius r, thickness t with an initial through crack of length a. The titanium cylindrical shell is sealed on one edge and compression is applied on the other. An additional applied pressure can generates a stress and deformation field around the crack tip that has bending stresses and membrane stresses and appears as a bulge around the crack area. This paper give details of a simulation with FEA numerical analysis that determine governing instability conditions of a Titanium shell under particular loading conditions and to put in light the effect of bulging on the stress intensity factor at the crack tips. This bulging factor measures the severity of the stress intensity in the bulged crack compared to a plane shell subjected to equivalent loading conditions.

Info:

Periodical:

Advanced Materials Research (Volumes 264-265)

Edited by:

M.S.J. Hashmi, S. Mridha and S. Naher

Pages:

490-495

Citation:

F. Ayari et al., "Numerical Study of Cracked Titanium Shell under Compression", Advanced Materials Research, Vols. 264-265, pp. 490-495, 2011

Online since:

June 2011

Export:

Price:

$38.00

[1] Characteristics of aircraft structural and materials, Material Handbook.

[2] R. Rolfes, R. Zimmermann, POSICOSS improved postbuckling simulation for design of fibre composite stiffened fuselage structures, Composite Structures, 73(2) (2006) pp.171-174.

DOI: https://doi.org/10.1016/j.compstruct.2005.11.041

[3] R. Degenhardt, R. Rolfes, R. Zimmermann, K. Rohwer, COCOMAT - Improved MATerial Exploitation at Safe Design of Composite Airframe Structures by Accurate Simulation of Collapse, Composite Structures, 73 (2006) pp.175-178.

DOI: https://doi.org/10.1016/j.compstruct.2005.11.042

[4] L. Krog, Application of Topology, Sizing and Shape Optimization Methods to Optimal Design of Aircraft Components. Solid Mechanics and Its Applications, 137(6) (2006) pp.239-248.

[5] C. Meeks, E. Greenhalgh, B.G. Falzon, Stiffener debonding mechanisms in post-buckled CFRP aerospace panels. Composites: Part A 36 (2005) p.934–946.

DOI: https://doi.org/10.1016/j.compositesa.2004.12.003

[6] A.B. Clarke, E. Greenhalgh, B. Millson, C. Jones, Investigation of the impact response of a CFRP wingbox under load for impact energies above the damage threshold, AIAA-2001-1389, AIAA/ASME/ASCE/AHS/ASC.

DOI: https://doi.org/10.2514/6.2001-1389

[7] Structures, Structural Dynamics, and Materials Conference and Exhibit, 42nd, Seattle, WA, Apr. 16-19, (2001).

[8] J.A. Collins and S.R. Daniewicz, Failure Modes: Performance and Service Requirements for Metals, M. Kutz (editor), Handbook of Materials Selection, John Wiley and Sons, 2002, pp.705-773.

DOI: https://doi.org/10.1002/9780470172551.ch25

[9] Visual Examples of Various Structural Failure Modes, Naval Postgraduate School, www. nps. navy. mil/avsafety/gouge/ structures/structures. ppt.

[10] Ductile and Brittle Fractures, Metals Handbook, 9th Edition, Vol. 11: Failure Analysis and Prevention, ASM International, 1986, pp.82-101.

[11] Ayari Fayza Lazghab Tarek Chelbi Lotfi; Parametric Study of Crack Growth In Cylindrical Aluminium Shells with Inner reinforcing foam layer, Fatigue design 2005- Senlis Paris.

DOI: https://doi.org/10.1007/s10704-007-9093-2

Fetching data from Crossref.
This may take some time to load.