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International Journal of Aerospace Engineering
Volume 2015, Article ID 723487, 8 pages
Research Article

Stress Distribution on Sandwich Structure with Triangular Grid Cores Suffered from Bending Load

Liaoning Key Laboratory of General Aviation and Liaoning Key Laboratory of Composite Manufacture technology, Shenyang Aerospace University, Shenyang 110136, China

Received 22 February 2015; Revised 13 May 2015; Accepted 18 May 2015

Academic Editor: Ronald M. Barrett

Copyright © 2015 Cui Xu et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


Triangular grid reinforced by carbon fiber/epoxy (CF/EP) was designed and manufactured. The sandwich structure was prepared by gluing the core and composite skins. The mechanical properties of the sandwich structure were investigated by the finite element analysis (FEA) and three-point bending methods. The calculated bending stiffness and core shear stress were compared to the characteristics of a honeycomb sandwich structure. The results indicated that the triangular core ultimately failed under a bending load of 11000 N; the principal stress concentration was located at the loading region; and the cracks occurred on the interface top skin and triangular core. In addition, the ultimate stress bearing of the sandwich structure was 8828 N. The experimental results showed that the carbon fiber reinforced triangular grid was much stiffer and stronger than the honeycomb structure.