Stability and vibration analysis of GOri metamaterial sandwich cylindrical panel supported by elastic foundation
Composite Structures, cilt.394, 2026 (SCI-Expanded, Scopus)
- Yayın Türü: Makale / Tam Makale
- Cilt numarası: 394
- Basım Tarihi: 2026
- Doi Numarası: 10.1016/j.compstruct.2026.120671
- Dergi Adı: Composite Structures
- Derginin Tarandığı İndeksler: Science Citation Index Expanded (SCI-EXPANDED), Scopus, Chimica, Compendex, INSPEC, Academic Search Ultimate (EBSCO), Engineering Source (EBSCO)
- Anahtar Kelimeler: Aerodynamic stability, Graphene origami, Higher–order sinusoidal shear deformation theory, Piezoelectric nanocomposites, Temperature-dependent properties
- Akdeniz Üniversitesi Adresli: Evet
Özet
In the current work, the aerodynamic behavior and free vibration characteristics of a circular cylindrical sandwich panel are investigated. The panel features a core reinforced with graphene origami (GOri) particles, while the face sheets are reinforced with carbon nanotube (CNT) inclusions. The structure lies on a Pasternak elastic foundation and is subjected to thermal loading as well as a three–dimensional electric field, with all material properties considered temperature–dependent. In addition, the face sheets exhibit piezoelectric properties. The panel is exposed to a supersonic airflow, representing the aerodynamic loading condition assumed in this study. To model the distribution of GOri particles through the core thickness, four distinct patterns are adopted. Likewise, three forms of CNT alignment throughout the face sheets’ thickness are utilized to accurately simulate the piezoelectric layers. Using the higher–order sinusoidal shear deformation theory (HSSDT) in conjunction with Hamilton's principle, a unified formulation is developed to capture the coupled aerodynamic, thermal, and electromechanical behavior of the GOri–core/CNT–reinforced cylindrical sandwich panel. Under simply supported boundary conditions, the formulated equations are solved through the Galerkin method to examine both aeroelastic and free vibration behaviors of the structure. The accuracy of the results and the reliability of the developed code are verified by comparing them with previously published studies. The effects of several key parameters including ambient temperature, various distributions of GOri and CNT particles, geometric characteristics of the cylindrical panel, the folding degree of GOri–reinforced structures, and the applied electric voltage are thoroughly examined. The obtained results reveal that increasing temperature causes a simultaneous reduction in both the nondimensional critical aerodynamic pressure and the nondimensional natural frequencies. For the considered temperature variations of ΔT = 0, 50, and 80 K, the corresponding nondimensional critical aerodynamic pressures are 4.34, 3.98, and 3.45, respectively. The results provide new insights into how nano–reinforcement architecture and thermal environments interact to influence aeroelastic stability boundaries and vibration characteristics of multifunctional sandwich structures, which is particularly relevant for next–generation aerospace panels operating under coupled thermo–aerodynamic conditions.