Constitutive Behavior and Ballistic Performance of Aerospace 2A16 Aluminum Alloy under Different Impact Velocities
Publication: Journal of Aerospace Engineering
Volume 35, Issue 4
Abstract
2A16 aluminum alloys possess outstanding mechanical characteristics such as high specific strength and remarkable heat-resistance capacity. Figuring out the dynamic mechanical performance of 2A16 aluminum alloy over a large range of strain rates is beneficial to further broaden its application as crucial civil and military structures under extreme loading. This paper mainly focused on the mechanical properties and ballistic impact capacity of 2A16 aluminum alloy under different strain rates. Firstly, the quasi-static, intermediate strain rates and high strain rate mechanical experiments of 2A16 aluminum alloy specimens were conducted using an electronic universal testing machine, a high velocity hydraulic servotesting machine, and a split Hopkinson pressure bar (SHPB) at room temperature, which aims to acquire its dynamic mechanical properties at different strain rates and the fracture behaviors under different stress conditions. Then, the modified Johnson-Cook constitutive model and the Johnson-Cook fracture model were fitted based on the stress-strain relationships obtained from the tests. Finally, the ballistic impact experiments were carried out by a spherical nosed projectile striking on square 2A16 aluminum plates with the incident velocities ranging from . Numerical simulations based the nonlinear explicit finite-element (FE) code Ls-dyna were conducted to reproduce the ballistic impact tests. The ballistic limit velocity of 2A16 aluminum was obtained through the Recht-Ipson empirical model and the predicted results agreed well with the numerical results. The results obtained from this study can contribute to the design and optimization of 2A16 aluminum aerospace engineering structures with better impact protection capacity.
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Data Availability Statement
All the data, models, or codes that support the findings of this study are available from the corresponding author upon the reasonable request.
Acknowledgments
The work described in this paper is financially supported by the National Natural Science Foundation of China (Grant No. 12002027), the Aeronautical Science Foundation of China (Grant No. 201941051001), and the Special Research on Civil Aircraft (Grant No. MJ-2017-F15). The authors would like to gratefully acknowledge this support.
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Published In
Journal of Aerospace Engineering
Volume 35 • Issue 4 • July 2022
Copyright
© 2022 American Society of Civil Engineers.
History
Received: Oct 7, 2021
Accepted: Feb 3, 2022
Published online: Mar 17, 2022
Published in print: Jul 1, 2022
Discussion open until: Aug 17, 2022
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