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Open AccessArticle

SPH-FEM Design of Laminated Plies under Bird-Strike Impact

1
College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing 211100, China
2
Commercial Aircraft Engine Co., LTD, Aero Engine Cooperation of China, Shanghai 201100, China
*
Authors to whom correspondence should be addressed.
Aerospace 2019, 6(10), 112; https://doi.org/10.3390/aerospace6100112
Received: 10 September 2019 / Revised: 1 October 2019 / Accepted: 3 October 2019 / Published: 7 October 2019
(This article belongs to the Special Issue Crashworthiness Design for Aviation Safety)
Composite laminates can potentially reduce the weight of aircrafts; however, they are subjected to bird strike hazards in civil aviation. To handle their nonlinear dynamic behaviour, in this study, the impact damage of composite laminates were numerically evaluated and designed by means of smoothed particle hydrodynamics (SPH) and the finite element method (FEM) to simulate the interaction between bird projectiles and the laminates. Attention was mainly focused on the different damage modes in various laminates’ plies induced by bird impact on a square laminated plate. A continuum damage mechanics approach was exploited to simulate damage initiation and evolution in composite laminates. Damage maps were computed with respect to different ply angles, i.e., 0°, 45° and −45°. The damage distributions were comparatively investigated, and then the ply design was considered for crashworthiness improvement. The results aim to serve as a design guideline for future prototype-scale bird strike studies of complex laminated structures. View Full-Text
Keywords: bird strike; composite laminates; ply angles; impact damage; SPH-FEM bird strike; composite laminates; ply angles; impact damage; SPH-FEM
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MDPI and ACS Style

Zhou, Y.; Sun, Y.; Huang, T. SPH-FEM Design of Laminated Plies under Bird-Strike Impact. Aerospace 2019, 6, 112.

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