Determining effects of impact loading on residual strength of fiber-metal laminates with grid-characteristic numerical method
| Autor: | Igor B. Petrov, A. V. Vasyukov, V. I. Golubev, K. A. Beklemysheva |
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| Rok vydání: | 2021 |
| Předmět: |
0209 industrial biotechnology
Materials science Composite number Aerospace Engineering 02 engineering and technology Low-velocity impact 01 natural sciences 010305 fluids & plasmas Stress (mechanics) 020901 industrial engineering & automation Numerical modeling 0103 physical sciences Fiber Full cycle Motor vehicles. Aeronautics. Astronautics Carbon fiber reinforced polymer business.industry Mechanical Engineering Numerical analysis TL1-4050 Structural engineering Grid Residual strength Fiber-metal laminate Grid-characteristic method business |
| Zdroj: | Chinese Journal of Aeronautics, Vol 34, Iss 7, Pp 1-12 (2021) |
| ISSN: | 1000-9361 |
| Popis: | The Grid-Characteristic numerical Method (GCM) that is quite common in solving aero and hydrodynamic problems can also be applied for mechanics of solids. It allows to implement complex border and contact conditions, including the non-reflecting border and the destructible contact. Both this conditions are very important for the precise and effective modeling of Low-Velocity Impacts (LVI) on fiber and Fiber-Metal Laminates (FML) and the resulting Barely Visible Impact Damage (BVID) that influences the residual strength of a composite aircraft part. BVID is the type of damage that is not visible by the naked eye and can be hardly detected by a standard ultrasound equipment that is used for regular maintenance. It can appear during any weak impacts like bird strike or hail. Determining its influence on the residual strength of the part is very important to define the priorities of development of ultrasound diagnostics. In this paper, the GCM was applied for a full cycle of loading of an FML aircraft cover part. The FML consisted of a Carbon Fiber Reinforced Polymer (CFRP) and a single titanium layer on the upper surface. The cycle of loading in a single calculation consisted of an LVI caused by a small striker and a comparatively slow compressive in-plane loading. Three-dimensional patterns of velocity and stress distributions over the time of calculation are given. Destruction patterns, obtained via the Hashin failure criterion are given and analyzed. |
| Databáze: | OpenAIRE |
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