Impact Damage Characteristics of Carbon Fibre Metal Laminates: Experiments and Simulation
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Impact Damage Characteristics of Carbon Fibre Metal Laminates: Experiments and Simulation Y. Shi 1 & C. Pinna 2 & C. Soutis 3 Received: 4 February 2020 / Accepted: 26 March 2020/ # The Author(s) 2020
Abstract
In this work, the impact response of carbon fibre metal laminates (FMLs) was experimentally and numerically studied with an improved design of the fibre composite lay-up for optimal mechanical properties and damage resistance. Two different stacking sequences (Carall 3–3/2–0.5 and Carall 5–3/2–0.5) were designed and characterised. Damage at relatively low energy impact energies (≤30 J) was investigated using Ultrasonic C-scanning and X–ray Computed Tomography (X-RCT). A 3D finite element model was developed to simulate the impact induced damage in both metal and composite layers using Abaqus/Explicit. Cohesive zone elements were introduced to capture delamination occurring between carbon fibre/epoxy plies and debonding at the interfaces between aluminium and the composite layers. Carall 5–3/2–0.5 was found to absorb more energy elastically, which indicates better resistance to damage. A good agreement is obtained between the numerically predicted results and experimental measurements in terms of force and absorbed energy during impact where the damage modes such as delamination was well simulated when compared to non-destructive techniques (NDT). Keywords Fibre metal laminates (FMLs) . Impact damage . Damage assessment . Ultrasonic Cscan . X-ray computed tomography (X-RCT), finite element analysis, cohesive zone elements
1 Introduction The drive for high-performance lightweight structures has led to the development of fibre metal laminates (FMLs) [1] made of thin metal sheets combined with fibre reinforced * C. Soutis [email protected]
1
Department of Mechanical Engineering, University of Chester, Thornton Science Park, Pool Lane, Chester CH2 4NU, UK
2
Department of Mechanical Engineering, The University of Sheffield, Mappin Street, Sheffield S1 3JD, UK
3
Aerospace Research Institute, The University of Manchester, Sackville Street, Manchester M13 9PL, UK
Applied Composite Materials
polymers [2]. This hybrid structure offers improved mechanical properties, by combining the benefits from both metal and composite components, such as good compression, impact and fatigue properties with excellent damage resistance due to the effect of crack bridging, which can significantly slow down crack growth. In particular, the fibre reinforced composite layers can reduce stresses in metal layers and therefore, help to absorb more impact energy compared to monolithic metallic materials when subjected to external impact loading to exhibit a high penetration resistance. Depending on such benefits of mechanical properties improved, FMLs have been widely used for applications in aircraft structures, such as the commercially developed Glare in skin panels for the fuselage of Airbus A380. As competition for the application of this kind of hybrid composite structures to aircraft is growing, the characte
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