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C. NICULIŢĂ1,* , S. VLASE1, A. BENCZE1, M. MIHĂLCICĂ1, M. R. CALIN2, L. SERBINA2
This paper is proposing a method for determining the optimum stacking in a composite laminate material using finite elements method program for a specific application (the skin panel used for the adaptive wing). The main area of application for this method refers to the wings of the adaptive aircrafts, where the material of the wing's skin is requested to provide good strength while allowing large deformations. This optimization can lead to the reduction of the technological and operational costs. The analysis and result interpretation can then be extrapolated to similar materials with bigger plies stacking..
Adaptive wing, Wing structure, Skin plate, Composite materials, Laminate, Stacking, Stress, Deformation.
C. NICULIŢĂ, S. VLASE, A. BENCZE, M. MIHĂLCICĂ, M. R. CALIN, L. SERBINA, Optimum stacking in a multi-ply laminate used for the skin of adaptive wings, Optoelectronics and Advanced Materials - Rapid Communications, 5, 11, November 2011, pp.1233-1236 (2011).
Submitted at: May 9, 2011
Accepted at: Nov. 23, 2011
Optoelectronics and Advanced Materials - Rapid Communications
(2023): 0.5 - 2023 Journal Citation Reports (Clarivate Analytics, 2024)
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