Failure analysis of composite bolted joints by an experimental and numerical approach
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(11) https://oatao.univ-toulouse.fr/20780
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(14) . Montagne, Benoît and Lachaud, Frédéric and Paroissien, Eric and Martini, Dominique Failure analysis of composite bolted joints by an experimental and numerical approach. (2018) In: 18th European Conference on Composite Materials (ECCM18), 24 June 2018 - 28 June 2018 (Athens, Greece).. .
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(24) 18th European Conference on Composite Materials – Athens (Greece) – 24-28 June 2018 Financements. Failure analysis of composite bolted joints by an experimental and numerical approach 1Institut. B. Montagne1, F. Lachaud1, E. Paroissien1 and D. Martini2 Clément Ader (ICA), Université de Toulouse, ISAE-SUPAERO, IMT Mines Albi, UTIII, INSA, CNRS, 3 rue Caroline Aigle 31400 Toulouse, France Email: benoit.montagne@isae-supaero.fr , frederic.lachaud@isae-supaero.fr , eric.paroissien@isae-supaero.fr 2Dassault Aviation, 78 Quai Marcel Dassault 92210 Saint-Cloud, France Email: dominique.martini@dassault-aviation.com Keywords : Composite material, bolted joint, finite element analysis. Introduction and context Falcon 7X: 250 000 fasteners. Source NIAR. Studied design parameters • End distance P • Width 2D • Load orientation. Rafale: 300 000 fasteners. Bearing. Net section Cleavage Cleavage/net Shearout section. Aircraft composite content (% weight). • Few composite parts on Falcon aircrafts • Need to master composite bolted joint behavior to satisfy performance and safety requirements. D P. Failure modes of composite bolted joints. Objective: Define the necessary numerical modelling complexity for characterizing the effects of the design parameters on the failure modes of composite bolted joints. Two-dimensional finite element analysis. Experimental results and database analysis Experimental settings for tests on supported single shear specimens Aluminium plate. Extensometer. Load. Load extension curve. Bearing Cleavage Net section. 0°. 45°. 90°. Composite plate 0. 1 2 Displacement measured by extensometer (mm). • Bearing stress at failure = t : thickness. 3. φ : bolt diameter. ϵ. Criteria applied on each plies orientation: • Maximal stress criterion (A) • Modified Hashin’s criteria (B). Influence of the end distance Bearing stress at failure. Bearing stress at failure. D=2.5φ 1. Cleavage Bearing 0 0. 1. 2 P/φ. 3. 4. D=1.5φ 1. Cleavage. / Net section. 0 0. 1. 2. 3. 4. P/φ. Influence of the width Bearing stress at failure. Bearing stress at failure. P=3φ 1. Bearing. Net section 0 0. 1. 2. 3. in the different plies orientation (here P=3φ and D=2.5φ ). /. • Net section (criteria on 0° plies) • Cleavage (criteria on 90°) • Bearing (criteria on 0° and ±45°) Net section failure. /. Cleavage failure. P=1.5φ 1. Cleavage. Cleavage. 0 0. 1. D/φ. 2. 3. D/φ. Bearing failure. Influence of the load orientation Bearring stress at failure. • FEM developed on Samcef Software (SIEMENS PLM Software) • Linear elastic materials (for bolt and composite plate) • Composite membrane elements. T700/M21. IMS977-2. 1. 0 0. Bearing Cleavage Net section Shearout. 50/20/20/10 stacking sequence 1 50/20/20/10 stacking sequence 2 20. 40 60 80 Orientation of the 0° plies. 100. L1 : 45/20/20/15 L2 : 45/24/24/7 L3 : 35/20/20/25. Perspectives. Conclusions Experimental database analysis: Influence of the design parameters on failure modes and stresses: • P is the most important parameter • D and the load orientation have a lower influence. Numerical 2D model: • Dispersions of criteria generally higher than experimental data • Simple macroscopic criteria do not always predict failure • Significant effect of shear. • Improving the FE modeling: Secondary bending effect Non linear behavior of • Out of plane effect modifying the composite material: stress field distribution • Identify the role of each damage on the Fastener modelled different failure modes with contact element on Samcef Acknowledgement : ISAE Supaero, Dassault Aviation and DGAC.
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