Abstract
Carbon Fibres Reinforced Plastics composites have been demonstrated particularly suitable for aerospace structural applications due to their high specific strength and stiffness. Nevertheless, the relevant costs related to composites manufacturing and the difficulties in predicting their failure mechanisms have considerably slowed down their integration in the aerospace industry. Furthermore, the lack of robust numerical tools, able to take into account the damage tolerance of composite structures, especially in the preliminary design phases, has led to an over-conservative design, not fully realising the promised economic benefits. Among their several and complex failure mechanisms, composite structures have been demonstrated to be highly sensitive to delaminations arising after impact with foreign objects or caused by manufacturing defects. Hence, in order to design less conservative aerospace composite structures, it is mandatory to account for the effects of delaminations and their evolution even in the earlier stages of the design process. In order to achieve this goal, newer and faster numerical procedures representing the main phenomenological features governing the structural behaviour of damage tolerant composite structures, such as the delamination growth, needs to be developed.Thus, the study presented in this chapter has been aimed at developing a linear approach useful to improve the preliminary design and optimisation of stiffened composite panels tolerant to low velocity impacts induced damage.
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References
Ashizawa, M.: Fast interlaminar fracture of a compressively loaded composite containing a defect. In: Proceedings of the Fifth DOD/NASA Conference on Fibrous Composites in Structural Design. NASA Ames Research Center, pp. 1–269 (1981)
Ramkumar, R.L.: Fatigue Degradation in compressively loaded composite laminates. NASA CR-165681 (1981)
Ramkumar, R.L.: Performance of a quantitative study of instability-related delamination growth. NASA CR-166046 (1983)
Byers, B.A.: Behaviour of damaged graphite/epoxy laminates under compression loading. NASA CR-159293 (1980)
Chai, H., Knauss, W.G., Babcock, C.D.: Observation of damage growth in compressively loaded laminates. J. Exp. Mech. 23(3), 329–337 (1983)
Arai, M., Noro, Y., Sugimoto, K.-I., Endo, M.: Mode I and mode II interlaminar fracture toughness of CFRP laminates toughened by carbon nanofiber interlayer. Compos. Sci. Technol. 68(2), 516–525 (2008)
Tong, L., Sun, X., Tan, P.: Effect of long multi-walled carbon nanotubes on delamination toughness of laminated composites. J. Compos. Mater. 42(1), 5–23 (2008)
Yokozeki, T., Aoki, Y., Ogasawara, T.: Experimental characterization of strength and damage resistance properties of thin-ply carbon fiber/toughened epoxy laminates. Compos. Struct. 82(3), 382–389 (2008)
Gordnian, K., Hadavinia, H., Mason, P.J., Madenci, E.: Determination of fracture energy and tensile cohesive strength in mode I delamination of angle-ply laminated composites. Compos. Struct. 82(4), 577–586 (2008)
Whitcomb, J.D.: Approximate analysis of postbuckled through-the-width delaminations. Compos. Technol. Rev. 4(3), 71–77 (1982)
Whitcomb, J.D.: Parametric analytical study of instability-related delamination growth. Compos. Sci. Technol. 25(1), 18–48 (1986)
Chai, H., Babcok, C.D., Knauss, W.G.: One delamination modelling of failure in laminated plates by delamination buckling. Int. J. Solids. Struct. 17(1), 1069–1083 (1981)
Shivakumar, K.N., Whitcomb, J.D.: Buckling of a sublaminate in a quasi-isotropic composite laminate. Int. J. Compos. Mater. 19, 2–18 (1985)
Whitcomb, J.D., Shivakumar, K.N.: Strain-energy release rate analysis of a laminate with a postbuckled delamination. numerical methods in fracture mechanics. NASA TM-89091 (1987)
Kim, H.J., Hong, C.S.: Buckling and postbuckling behaviour of composite laminates with an embedded delamination. In: Proceedings of ICCM-10 Whistler, B.C. (1995)
Singh, K.L., Dattaguru, B., Ramamurthy, T.S., Mangalgiri, P.D.: Delamination tolerance studies in laminated composite panels. Sadhana (printed in India) 25(4), 409–422 (2000)
Shahwan, K., Waas, A.M.: Unilateral buckling of rectangular plates. Int. J. Solids Struct. 31(1), 75–89 (1994)
Shahwan, K., Waas, A.M.: Buckling of unilaterally constrained plates: application to the study of delaminations in layered structures. J. Franklin Inst. 335B(6), 1009–1039 (1998)
Whitcomb, J.D.: Analysis of a laminate with a postbuckled embedded delamination, including contact effects. Int. J. Compos. Mater. 26(10), 1523–1535 (1992)
Whitcomb, J.D.: Three dimensional analysis of a postbuckled embedded delamination. Int. J. Compos. Mater. 23, 862–889 (1989)
Perugini, P., Riccio, A., Scaramuzzino, F.: Influence of delamination growth and contact phenomena on the compressive behaviour of composite panels. Int. J. Compos. Mater. 33(15), 1433–1456 (1999)
Riccio, A., Perugini, P., Scaramuzzino, F.: Modelling compression behaviour of delaminated composite panels. Comput. Struct. 78, 73–81 (2000)
Nilsson, K.-F., Thesken, J.C., Sindelar, P., Giannakopoulos, A.E., Storakers, B.: A theoretical and experimental investigation of buckling induced delamination growth. J. Mech. Phys. Solids. 41(4), 749–782 (1993)
Gaudenzi, P., Perugini, P., Riccio, A.: Post-buckling behaviour of composite panels in the presence of unstable delaminations. Compos. Struct. 51(3), 301–309 (2001)
Riccio, A., Perugini, P., Scaramuzzino, F.: Embedded delamination growth in composite panels under compressive load. Compos. B Eng. 32(3), 209–218 (2001)
Riccio, A., Scaramuzzino, F., Perugini, P.: Influence of contact phenomena on embedded delamination growth in composites. AIAA J. 41(5), 933–940 (2003)
Davies, G.A.O., Hitchings, D., Ankersen, J.: Predicting delamination and debonding in modern aerospace composite structures. Compos. Sci. Technol. 66, 846–854 (2006)
De Borst, R., Remmers, J.J.C.: Computational modelling of delamination. Compos. Sci. Technol. 66, 713–722 (2006)
Allix, O., Blanchard, L.: Mesomodelling of delamination: towards industrial applications. Compos. Sci. Technol. 66, 731–744 (2006)
Gudmundson, P.: Micromechanically based constitutive models for damage evolution in composite laminates. Int. J. Damage Mech. 9(1), 29–39 (2000)
ABAQUS MANUAL (revision 6.5-1): Theory
Greenhalgh, E., Singh, S., Hughes, D., Roberts, D.: Impact damage resistance and tolerance of stringer stiffened composite structures. Plast. Rubber Compos. Process. Appl. 28(5), 228–251 (1999)
Greenhalgh, E., Meeks, C., Clarke, A., Thatcher, J.: The effect of defects on the performance of post-buckled CFRP stringer-stiffened panels. Compos. A Appl. Sci. Manuf. 34(7), 623–633 (2003)
Greenhalgh, E., Singh, S., Nilsson, K.-F.: Mechanisms and modeling of delamination growth and failure of carbon-fiber reinforced skin-stringer panels. ASTM Spec. Tech. Publ. 1383, 49–71 (2000)
Suemasu, H., Kurihara, K., Arai, K., Majima, O., Ishikawa, T.: Compressive property degradation of composite stiffened panel due to debonding and delaminations. Adv. Compos. Mater: Official J. Jpn Soc. Compos. Mater. 15(2), 139–151 (2006)
ANSYS MANUAL (revision 5) Volume III: Elements DN-R300:50-3
Riccio, A., Gigliotti, M.: A novel numerical delamination growth approach for the preliminary design of damage tolerant composite structures. J. Compos. Mater. 41(16), 1939–1960 (2007)
Faggiani, A., Falzon, B.G.: Optimization strategy for minimizing damage in postbuckling stiffened panels. AIAA J. 45(10), 2520–2528 (2007)
Guédra-Degeorges, D.: Recent advances to assess mono-and multi-delaminations behaviour of aerospace composites. Compos. Sci. Technol. 66, 796–806 (2006)
Bruno, D., Greco, F.: Mixed mode delamination in plates: a refined approach. Int. J. Solids Struct. 38, 9149–9177 (2001)
Gaudenzi, P., Perugini, P., Spadaccia, F.: Post-buckling analysis of a delaminated composite plate under compression. Compos. Struct. 40(3), 231–238 (1998)
Krueger, R.: The virtual crack closure technique: history, approach and applications. NASA/CR-2002-211628, ICASE Report No. 2002-10 (2002)
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Riccio, A., Damiano, M. (2015). A Fast Numerical Methodology for Delamination Growth Initiation Simulation. In: Riccio, A. (eds) Damage Growth in Aerospace Composites. Springer Aerospace Technology. Springer, Cham. https://doi.org/10.1007/978-3-319-04004-2_9
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