Ehsan Arshid^*

CMES-Computer Modeling in Engineering & Sciences, Vol.146, No.1, 2026, DOI:10.32604/cmes.2025.074898 - 29 January 2026

Abstract In this work, a computational modelling and analysis framework is developed to investigate the thermal buckling behavior of doubly-curved composite shells reinforced with graphene-origami (G-Ori) auxetic metamaterials. A semi-analytical formulation based on the First-Order Shear Deformation Theory (FSDT) and the principle of virtual displacements is established, and closed-form solutions are derived via Navier’s method for simply supported boundary conditions. The G-Ori metamaterial reinforcements are treated as programmable constructs whose effective thermo-mechanical properties are obtained via micromechanical homogenization and incorporated into the shell model. A comprehensive parametric study examines the influence of folding geometry, dispersion arrangement, More >

Zheng Wu¹, Pai Liu¹, Zhan Kang¹, Yiqiang Wang^1,*

The International Conference on Computational & Experimental Engineering and Sciences, Vol.29, No.2, pp. 1-2, 2024, DOI:10.32604/icces.2024.011044

Abstract Honeycomb sandwich structures (HSSs) consist of lightweight cores arranged in periodic polygons [1] between two face sheets. They are widely used in the aerospace industry due to their lightweight but superior strength [2] and energy absorption [3]. As extremely high temperatures might be applied, the sandwich structures may suffer from thermal buckling failure [4] due to thin face walls [5]. This paper designs a new type of HSSs for pursuing optimal thermal buckling strength. The design idea is to replace the vertical straight walls in the honeycomb cores with curved walls. An optimization problem is… More >

Le-Chung Shiau¹, Shih-Yao Kuo²

CMC-Computers, Materials & Continua, Vol.5, No.3, pp. 213-222, 2007, DOI:10.3970/cmc.2007.005.213

Abstract A high precision high order triangular plate element is developed for the linear flutter analysis of thermally buckled composite sandwich plates. Due to uneven thermal expansion in the two local material directions, the buckling mode of the plate may be shifted from one pattern to another for certain fiber orientation or plate aspect ratio as the aerodynamic pressure is present. This buckle pattern change alters the frequencies and modes of the plate and that in turn changes the flutter coalescent modes. Numerical results show that temperature has a destabilizing effect on the flutter boundary but More >