Static and Fatigue Characteristics of Pinned Metal-Composite Joints
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Metal-composite joining methods currently rely almost exclusively on the adhesive bonding, the application of mechanical fasteners or a combination of the methods, the pros and cons of which are well known. In this article, a manufacturing-oriented solution for increasing the static and fatigue characteristics of metal composite bolted T-joints loaded in the out-of-plane direction by reinforcing the composite basement with a thin metal plate having die cut pins is proposed. Static load–displacement and fatigue life curves were obtained experimentally for different types of joints. The results obtained showed that, for a fiberglass/epoxy laminate, the solution proposed increased its static and fatigue failure loads by 64 and 50% respectively. It was also found that pinned adhesive joints were more effective than the conventional bolted ones at high-cycle loadings (the number of cycles exceeded 104).
Keywordspinned metal-composite joints out-of-plane loading interlaminar static and fatigue strengths,pullouttest
This work was performed with the financial support FP7 KhAI-ERA project “Integrating the National Aerospace University “KhAI” into ERA” (GA No 294311) and NETME Centre built in the frame NETME Centre project “New Technologies for Mechanical Engineering” (Reg. No. CZ.1.05/2.1.00/01.0002) with the financial support from the Operational Program Research and Development for Innovations of Czech Republic.
- 1.A. C. Nogueira, K. Drechsler, and E. Hombergsmeier, “Properties and failure mechanisms of 3D-reinforced joint,” JEC Composites Magazine, 69, 39-44 (2011).Google Scholar
- 3.T. Yang, J. Zhang, A. P. Mouritz, and C. H. Wang, “Healing of carbon fiber–epoxy composite T-joints using mendable polymer fiber stitching,” Composites: Part B, 45, No. 1, 1499-1507 (2013).Google Scholar
- 15.I. S. Karpov, Joining of Parts and Units Made of Composite Materials [in Russian], National Aerospace University“Kharkov Aviation Institute,” Kharkov (2006).Google Scholar
- 16.I. S. Karpov, Design of Composite Parts and Units [in Russian], National Aerospace University “Kharkov Aviation Institute,” Kharkov (2010).Google Scholar
- 17.F. Bianchi, Numerical modelling of across-the-thickness reinforced structural joints, Ph.D. thesis. Cranfield, Cranfield University (2012).Google Scholar
- 19.J. T. Vazquez, B. Castanié, J. J. Barrau, and N. Swiergiel, “Multi-level analysis of low-cost Z-pinned composite joints: Part 1: Single Z-pin behavior,” Composites: Part A, 42, No. 12, 2070-2081 (2011).Google Scholar
- 20.J. T. Vazquez, B. Castanié, J. J. Barrau, and N. Swiergiel, “Multi-level analysis of low-cost Z-pinned composite joints: Part 2: Joint behavior,” Composites: Part A, 42, No. 12, 2082-2092 (2011).Google Scholar
- 24.Airbus Operations Gmbh., Method for connecting a fiber composite component to a structural component of an aircraft and spacecraft and a corresponding arrangement. Inventors: M. Pacchione and D. Furfari. US Patent Specification 20130149501. 13.06.2013.Google Scholar
- 30.H. Mick, “Micro-sculptures give metal the Velcro touch,” New Sci, 182, Iss. 2447, 8-21 (2004).Google Scholar