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Fracture in Composites - An Overview (Part I)

. Carlsson, P. Davies. Beam Analysis of Angle-ply Laminated End-notched Flexure Specimens. Composite Science and Technology   58 (1998), No. 4 , 1929-1938. Bullions, T. A., R. H. Mehta, B. Tan, J. E. McGrath, D. Kranbuehl, A. C. Loos. Mode I and Mode II Fracture Toughness of High-performance 3000 g mole -1 Reactive Ply(Etherimide)/carbon Fibre Composites. Composites Part A: Applied Science and Manufacturing , 30 (1999), No. 3 , 153-162. Broek, D. Elementary Engineering Fracture Mechanics, 4-th ed., The Netherlands

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Strain Energy Release Rate Determination in the Case of Mode II Crack in Overhanging Bilayered Composite Beam

References [1] Szekrenyes, A. Pre-stressed Composite Specimen for Mixed-mode I/II Crack- ing in Laminated Materials. Journal of Reinforced Plastics and Composites, 29 (2010), 3309-3321. [2] O’Brien, K. Characterization, Analysis and Prediction of Delamination in Com- posites Using Fracture Mechanics, NASA Langley Research Center, 2001. [3] Szekrenyes, A. Improved Analysis of the Modified Split-cantilever Beam for Mode-III Fracture. International Journal of Mechanical Sciences, 51 (2009), 682

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A Numerical Analysis of Selected Elastic-Plastic Fracture Parameters for DEN(T) Plates under Plane Strain Conditions

-for-service Network), Contract No. G1RT-CT-2001-05071. [11] O’Dowd N.P. (1995): Applications of two parameter approaches in elastic-plastic fracture mechanics . – Engineering Fracture Mechanics, vol.52, No.3, pp.445-465. [12] Ritchie R.O., Knott J.F. and Rice J.R. (1973): On the relationship between critical tensile stress and fracture toughness in mild steel . – Journal of the Mechanics and Physics of Solids, vol.21, pp.395-410. [13] Neimitz A., Graba M. and Gałkiewicz J. (2006): New formulation of the Ritchie, Knot and Rice hypothesis . – Proceedings of XVI

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Analysis of Fatigue Crack Growth in Ship Structural Details

al., Fatigue and fracture mechanics of high risk parts: application of LEFM & FMDM theory. New York: Chapman & Hall, 1997. 11. B. Farahmand : Fracture mechanics of metals, composites, welds, and bolted joints: application of LEFM, EPFM, and FMDM theory. Boston: Kluwer Academic Publishers, 2001. 12. S. Beden, et al.: Review of Fatigue Crack Propagation Models for Metallic Components. European Journal of Scientific Research, vol. 28, pp. 364-397, 2009. 13. H. A. Rothbart and T. H. Brown: Mechanical design handbook: measurement, analysis, and control

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Failure Mechanisms of Brittle Rocks under Uniaxial Compression

-191. [7] DYSKIN, A. V., E. SAHOURYEH, R. J. JEWELL. Influence of Shape and Locations of Initial 3-D Cracks on Their Growth in Uniaxial Compression. Engineering Fracture Mechanics, 70 (2003), 2115-2136. [8] HOEK, E., C. D. MARTIN. Fracture Initiation and Propagation in Intact Rock - A Review. Journal of Rock Mechanics and Geotechnical Engineering, 6 (2014), No. 4, 287-300. [9] HORII, H., S. NEMAT. Brittle Failure in Compression: Splitting, Faulting and Brittleductile Transition. J. Phil. Trans. R. Soc. London A, 139 (1986), 337

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Fracture in Composites - An Overview (Part II)

Fracture in Composites - An Overview (Part II)

An overview of the literature for the last twenty years on the fracture mechanics of unidirectional fibre reinforced polymer composites is presented. Pure mode (I, II, and III) as well as mixed mode longitudinal cracks (i.e., cracks that propagate along the fibres) are considered mainly. It is shown that the strain energy released rate is the most widely used parameter for fracture toughness characterization. Various solutions for determination of the strain energy release rate in composites using linear-elastic fracture mechanics are presented. Studies on fracture in composite sandwich structures are reviewed, too. Some analyses of damages and their influence on fracture behaviour also are considered. Topical problems of composite fracture mechanics are formulated.

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Application of J-Integral in the Case of a Single Crack in Cantilever Beam

References Siratori, M., T. Miesi, H. Matsusita. Computational Fracture Mechanics, Moscow, Mir, 1986 (in Russian). Ewalds, H. L., R. J. H. Wanhill. Fracture Mechanics, Hodder Headline PLC, 1984. Morozov, N. Mathematical Aspects of Fracture Mechanics, Moscow, Nauka, 1984 (in Russian). Matvienko, Y. Fracture Mechanics Models and Criteria, Moscow, Fizmatlit, 2006 (in Russian). Broek, D. Elementary Engineering Fracture Mechanics

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Numerical Calculation of the Aircraft Skin with Multi-Site Damage

/CR-1999-209115, Cornell University, Ithaca, New York USA 1999. Chen Ch.S., Wawrzynek P. A., Ingraffea A. R.: Methodology for Fatigue Crack Growth and Residual Strength Prediction with Applications to Aircraft Fuselages. "Computational Mechanics" 1997, pp. 527-532. Dawicke D. S., Newman J. C., Bieglow C. A.: Tree-Dimensional CTOA and constraint Effects During Stable Tearing in a Thin-Sheet Material . "Fracture Mechanics" 1995, Vol. 26, red. Reuter et al., American Society of Testing and materials, Philadelphia, pp

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Evaluation of the Compliance of Aircraft Wing Flap with Use of the Fracture Mechanics

Abstract

Research in the field of fracture mechanics and determination of material characteristics are used for practical purposes, such as the assessment of static and dynamic strength of structural components, analysis of their fatigue life or extending the life span of their operation. A structural component, considered to be safe from fatigue cracking point of view, was investigated and results were presented in this article. In particular, an analysis was made to determine the stress intensity factor for the cracked wing flap construction, based on static and fatigue tests, using the Irwin-Kies theory. The flap with a service crack was subjected to fatigue tests with a load similar to the one registered during flight measurements. The flap without a service crack was subjected to static tests, after cutting the cracks of specified lengths and shapes (similar to the service crack) in the skin of the flap. The article presents changing the length of the flap crack in subsequent load cycles, change in the maximum values of force and the crack opening displacement in subsequent load cycles, dependence of P-COD in the first and second stage of fatigue testing of the wing flap, dependence of the wing flap compliance on the length of the crack and experimentally determined dependence for wing flap. The occurrence of a flap crack up to approximately 230 mm does not cause a significant growth of the stress intensity factor.

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The Numerical Analysis of Weldability in the Design and Technological Processes Influence on the Exploitation Condition and Quality

References Ainsworth, R. A. et al., Methods for including constraint effects within the SINTAP procedures. Engineering Fracture Mechanics , Vol. 67, Issue 6, 2000. Broberg, K. B.: Computer demonstration of crack growth. International Journal of Fracture. 42, 1990. Burstow, M. C.: Analysis of welded joints. SIRIUS. 1996. David, S. A., Babu, S. S., Microstructure modelling in weld metal. Mathematical Modelling of Weld Phenomena 3. Edited by H. Cerjak

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