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Purpose: of this paper is comparison of impact delaminations in CFRP using different test methods. Design/methodology/approach: A comparison is made between the results of well-established techniques such as Ultrasonic Testing or micrographic cross-sections with the results of Microfocus Computed X-Ray Tomography. Findings: The findings show that both Ultrasonic Testing and μCT show a linear correlation between impact energy and delaminated area. However, μCT is able to detect significantly larger delaminated areas. Other findings were that the undamaged zone immediately underneath the contact point of the impactor is not a cylinder but a cone segment. The higher density of that compacted area could also be visualized. Research limitations/implications: The correlation between main impact parameters could be shown on the base of state of the art non-destructive testing. Originality/value: Impact delaminations in carbon fiber reinforced plastic have generated in a well-defined manner and a comparison is made between the results of well-established techniques such as Ultrasonic Testing (UT) or micrographic cross-sections with the results of Microfocus Computed X-Ray tomography (μCT).
Wydawca
Rocznik
Tom
Strony
128--138
Opis fizyczny
Bibliogr. 11 poz., rys.
Twórcy
autor
- Regensburg University of Applied Sciences, Faculty of Mechanical Engineering, Laboratory of Composite Technology (LFT), Galgenbergstrasse 30, 93053 Regensburg, Germany
autor
- Bundeswehr Research Institute for Materials and supplies,, Institutsweg 1, 85435 Erding, Germany
autor
- Regensburg University of Applied Sciences, Faculty of Mechanical Engineering, Laboratory of Composite Technology (LFT), Galgenbergstrasse 30, 93053 Regensburg, Germany
Bibliografia
- [1] N. N.http://www.hexcel.com/Resources/DataSheets/Prepreg-Data-Sheets/8552 eu.pdf, 12.07.2013
- [2] N. N.: DIN EN 7000-11: Aerospace - Non-metallic materials - Rules for drafting and presentation of Werkstofformen - Part 11: prepregs. German standard,
- [3] norm point Aviation (NL) at DIN Institute for Standardization e. V., Beuth Verlag GmbH, Berlin, 2000
- [4] N. N.: DIN EN 2564: Carbon fiber laminates. Determination of the fiber, resin and amount of pores. German standard, norm point Aviation (NL) at DIN Institute for Standardization e. V., Beuth Verlag GmbH, Berlin, 1998
- [5] N. N.: AITM 1.00.10: Fiber Reinforced Plastics. Determination of compression strength after impact. AIRBUS Industry Test Method, Lagnac Cedex, France, 1994.
- [6] W.J. Cantwell, J. Morton, The impact resistance of composites materials – a review. Composites 22/5 (1993).
- [7] W. Hilger, HFUS 2000 – Benutzerhandbuch. Ingenieurbüro Dr. Hilger, Braunschweig, 2000.
- [8] H. Sekine, N. Hu, H. Fukanaga, T. Natsume, Low-velocity impact response of composite laminates with a delamination. Mechanics of Composite Materials and Structures, 1998, 275-278
- [9] G. Zhou, L.J. Greaves, Damage resistance and tolerance of thick laminated woven roving GFRP plates subjected to low-velocity impact. Impact Behaviour of Fibre-Reinforced Composite Materials and Structures. CRC Press, Boca Raton (USA), 2000
- [10] T. M.Tan,; C.T. Sun, Use of statical indentation laws in the impact analysis of laminacted composite plates. Journal of Applied Mechanics, Transactions of the ASME 52/6 (1985.)
- [11] H.Y. ChoI,; C H. Lim, Low-velocity impact analysis of composite laminates using linearized contact law. Composite Structures 66 (2004) 125-132
Typ dokumentu
Bibliografia
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bwmeta1.element.baztech-fd74d87f-688b-4bdd-9701-f5e88b90a4b9