Investigation of Integral Composite T-Joints under Mixed Mode Loading

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This paper presents experimental and numerical results on the deformations and failureof integral composite T-joints subjected to a realistic combined tensile and bending (mixed mode)load case. For this reason, standard pull-off and mixed mode load cases are experimentally studiedby means of a novel test fixture which keeps the force angle constant to the T-joint’s base and allowsfor repositioning of the specimen in order to minimize constraining forces. Two types of specimenswith varying deltoid radius are investigated. Additionally, kinematically nonlinear numerical simulationsare performed to locate damage onset and deformations of the specimens. It is found that thesimulations are in good agreement with the experimental results.

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Edited by:

Luis Rodríguez-Tembleque, Jaime Domínguez and Ferri M.H. Aliabadi

Pages:

197-202

Citation:

F. Nolte et al., "Investigation of Integral Composite T-Joints under Mixed Mode Loading", Key Engineering Materials, Vol. 774, pp. 197-202, 2018

Online since:

August 2018

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$38.00

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[1] M. Burnazzi and R. Radespiel. Design and analysis of a droop nose for coanda flap applications. Journal of Aircraft, 51(5):1567-1579, (2014).

DOI: https://doi.org/10.2514/1.c032434

[2] J. Chen and D. Fox. Numerical investigation into multi-delamination failure of composite t-piece specimens under mixed mode loading using a modified cohesive model. Composite Structures, 94(6):2010-2016, (2012).

DOI: https://doi.org/10.1016/j.compstruct.2011.12.030

[3] R. D. Cope and R. B. Pipes. Design of the composite spar-wingskin joint. Composites, 13(1): 47-53, (1982).

DOI: https://doi.org/10.1016/0010-4361(82)90170-7

[4] F. Hélénon, M. R. Wisnom, S. R. Hallett, and R. S. Trask. Numerical investigation into failure of laminated composite t-piece specimens under tensile loading. Composites Part A: Applied Science and Manufacturing, 43(7):1017-1027, (2012).

DOI: https://doi.org/10.1016/j.compositesa.2012.02.010

[5] T. M. Koh, S. Feih, and A. P. Mouritz. Experimental determination of the structural properties and strengthening mechanisms of z-pinned composite t-joints. Composite Structures, 93(9): 2222-2230, (2011).

DOI: https://doi.org/10.1016/j.compstruct.2011.03.009

[6] S. Kumari and P. K. Sinha. Finite element analysis of composite wing t-joints. Jnl of Reinforced Plast and Composites, 21(17):1561-1585, (2002).

DOI: https://doi.org/10.1177/0731684402021017474

[7] S. K. Panigrahi and B. Pradhan. Development of load coupler profiles of spar wingskin joints with improved performance for integral structural construction of aircraft wings. Jurnal of Reinforced Plastics and Composites, 28(6):657-673, (2008).

DOI: https://doi.org/10.1177/0731684407086594

[8] H. J. Phillips and R. A. Shenoi. Damage tolerance of laminated tee joints in frp structures. Composites Part A: Applied Science and Manufacturing, 29(4):465-478, (1998).

DOI: https://doi.org/10.1016/s1359-835x(97)00081-x

[9] A. Puck and H. Schürmann. Failure analysis of frp laminates by means of physically based phenomenological models1. Composites Science and Technology, 58(7):1045-1067, (1998).

DOI: https://doi.org/10.1016/s0266-3538(96)00140-6

[10] P. Read and R. A. Shenoi. Fatigue behaviour of single skin frp tee joints. International Journal of Fatigue, 21(3):281-296, (1999).

DOI: https://doi.org/10.1016/s0142-1123(98)00075-9

[11] A. Schmitz and P. Horst. Bending deformation limits of corrugated unidirectionally reinforced composites. Composite Structures, 107:103-111, 2014. ISSN 0263-8223..

DOI: https://doi.org/10.1016/j.compstruct.2013.07.048

[12] R. S. Trask, S. R. Hallett, F. M. M. Helenon, and M. R. Wisnom. Influence of process induced defects on the failure of composite t-joint specimens. Composites Part A: Applied Science and Manufacturing, 43(4):748-757, (2012).

DOI: https://doi.org/10.1016/j.compositesa.2011.12.021

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