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Verification of Fastener Modeling Techniques for Joining Composite and Metallic Assemblies
ISSN: 0148-7191, e-ISSN: 2688-3627
Published September 28, 2010 by SAE International in United States
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Structural analysis of aircraft components has involved the use of finite element method (FEM) analysis for many years. The transition from all metallic aircraft to hybrid constructions of composite and metallic materials has added complexity. Analysts have traditionally viewed each component individually, with a simplified attaching procedure, and generated the corresponding interface loads. This can be critical to the design details since composite components are often critical for fastener loads. Traditional analysis techniques for composite materials are a combination of simplified assumptions and empirical test data. This approach worked well when both the modeling technique for the two mating structures and the interface were of the same order of complexity. The recent increase in computational capability has allowed analysts to create very detailed finite element models of the structural components and thus make more accurate predictions of strength and stiffness, leading to more weight efficient structure. This increased fidelity of the individual component models dictates that analysis of the attaching method must also be more rigorous. In recent years the ability to model the attachment interface has been developed for both metallic and composite materials with a perceived level of accuracy. This study uses the existing analytical tools and compares those with test data to verify the accuracy of the method and provides modeling guidelines for attaining appropriately accurate results.
CitationKitt, B. and Boshers, C., "Verification of Fastener Modeling Techniques for Joining Composite and Metallic Assemblies," SAE Technical Paper 2010-01-1831, 2010, https://doi.org/10.4271/2010-01-1831.
- MSC Nastran Quick Reference Guide 2004 The MacNeal-Schwendler Corporation Los Angeles, CA
- “Defining a standard formula and test-method for fastener flexibility in lap-joints” Morris, G. TU Delft 2004
- “Fastener Modeling for MSC. Nastran Finite Element Analysis” Rutman, A. Visoreanu, A. Parady, J. SAE and AIAA 2000 World Aviation Conference 2000
- “Fastener Modeling for Joining Parts Modeled by Shell and Solid Elements” Rutman, A. Boshers, C. Pearce, L. Parady, J. 2007 Americas Virtual Product Development Conference 2007
- “Fastener Modeling for Joining Composite Parts” Rutman, A. Boshers, C. Pearce, L. Parady, J. 2009 Americas Virtual Product Development Conference 2009
- “Preliminary Investigation of the Loads Carried by Individual Bolts in Bolted Joints” Tate, M. Rosenfeld, S. National Advisory Committee for Aeronautics Technical Note No. 1051 1946
- “Analytical and Experimental Investigation of Bolted Joints” Rosenfeld, S. National Advisory Committee for Aeronautics Technical Note No. 1458 1947
- “Critical Composite Joint Subcomponents, Analysis and Test Results” Bonin, B.L. NASA Contractor Report No. 3711 1983
- “Shear Fatigue Performance of Postbuckling Fibre Composite Panels” Noor, ICCM/9 Composites Properties and Applications VI