Experimental and numerical assessment of impact resistance of FMLs including one rubber layer
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(2020) 42:455
TECHNICAL PAPER
Experimental and numerical assessment of impact resistance of FMLs including one rubber layer Hamid Khajeh Arzani1 · Abdulreza Kabiri Ataabadi2 · Yoosof Chaparian1 Received: 22 March 2020 / Accepted: 21 July 2020 © The Brazilian Society of Mechanical Sciences and Engineering 2020
Abstract Fiber metal laminates have lately attracted considerable interest due to their diverse use in industrial sectors. Indeed, FMLs are virtually applied by combining both the metal and composite layers in order to achieve better outcomes. The preference of FML over metal or composite has been verified in many studies. The preliminary objective of the present study, however, is to make attempts to evaluate the influence of rubber layer on FML impact resistance once subjected to high-velocity impact. To this end, a numerical analysis is administered following an experiment. In this regard, the applied materials consist of 2024-T3 aluminum alloy, woven glass/epoxy prepreg and nitrile butadiene rubber. The steel projectile for impact tests was geometrically cylinder and flat-ended. It is noteworthy that all tests were run by a high-speed gas gun, and the numerical analysis was carried out in LS-DYNA software. Ultimately, the obtained results indicated that by inserting a rubber layer among the laminates, aluminum layer can bend further, and more kinetic energy can be dissipated from the projectile. Moreover, the special perforation energy and ballistic limit velocity, V50, increased dramatically. Keywords Fiber metal laminates · Special perforation energy · Ballistic limit velocity · LS-DYNA
1 Introduction As one of the most complicated struggles in solid mechanics, high-velocity impact has been—and will remain—a major topic of interest among many researchers specially in aerospace field [1–7]. In this respect, researchers have to fully comprehend and aptly analyze the process of projectile penetration in designing structures. In many studies, composites turned out to have a relatively poor resistance to perforation, when exposed to the high-velocity impact load by a low-mass projectile [8, 9]. Some studies [10–12] suggested that any impact load even with low energy could bring about damage, which in turn can lead to dramatic decline in the load-bearing capacity of the given component. Accordingly, an in-depth Technical Editor: João Marciano Laredo dos Reis. * Abdulreza Kabiri Ataabadi a.kabiri.at@mut‑es.ac.ir 1
Department of Mechanical and Aerospace Engineering, Malek Ashtar University of Technology, Isfahan, Iran
Department of Mechanical Engineering, Malek Ashtar University of Technology, Isfahan 83145/115, Iran
2
assessment of a great number of fractured composite components demonstrated a variety of failure mechanisms, like matrix cracking, fiber fracture, delamination and fiber matrix debonding [13]. In addition, thorough comprehension of the projectile penetration process is required in order to increase the impact resistance of aerospace structures and to overcome the existing drawback
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