Nonlinear wave dynamics and structural response of hybrid nanocomposite open shells under aerodynamic forces on a friction-coupled elastic foundation
SCIENTIFIC REPORTS, cilt.16, sa.1, 2026 (SCI-Expanded, Scopus)
- Yayın Türü: Makale / Tam Makale
- Cilt numarası: 16 Sayı: 1
- Basım Tarihi: 2026
- Doi Numarası: 10.1038/s41598-026-71917-0
- Dergi Adı: SCIENTIFIC REPORTS
- Derginin Tarandığı İndeksler: Science Citation Index Expanded (SCI-EXPANDED), Scopus, BIOSIS, Chemical Abstracts Core, EMBASE, MEDLINE, Directory of Open Access Journals, Zoological Record, Academic Search Ultimate (EBSCO), Natural Science Collection (ProQuest), Biological Science Database (ProQuest), Biomedical Reference Collection: Corporate Edition (EBSCO), Health Research Premium Collection (ProQuest)
- Açık Arşiv Koleksiyonu: AVESİS Açık Erişim Koleksiyonu
- Recep Tayyip Erdoğan Üniversitesi Adresli: Evet
Özet
It is extremely important to have information about the stability and wave propagation characteristics of the aircraft structure due to high-speed aerodynamic loads in order to design the next generation of flight vehicles. In this research work, a new coupled methodology between aerodynamics and foundation for nonlinear dispersion of a doubly curved nanocomposite fuselage panel in a supersonic flow regime is proposed. The material is made of an epoxy-based matrix reinforced by nanocrystalline alumina and is resting on a viscoelastic foundation with consideration of all possible interaction forces. Unlike the traditional aeroelastic theory, the proposed methodology offers a physically sound modification to the classical first-order supersonic piston theory. As a result, the aerodynamic loading is state-dependent and inherently dependent on the supporting medium, and the model naturally reduces to classical piston theory in the absence of any foundation effects. The deformation kinematics of the structure are formulated based on higher-order shear deformation theory having a hyperbolic shear strain distribution, while the geometric nonlinearity in the model has been accounted for by means of von K & aacute;rm & aacute;n strain-displacement relations. Hamilton's principle is utilized to develop the fully coupled nonlinear governing equations, and these governing equations have been validated by making extensive comparisons with published results as well as by a separate finite element formulation. The system of nonlinear algebraic equations obtained from the governing equations is solved using the harmonic balance method to determine dispersion characteristics along with nonlinear group and phase velocities. Extensive parametric studies show that the proposed fully coupled aeroelastic model is capable of predicting very complicated instability characteristics, flutter boundaries, wave propagation characteristics, and dispersion properties that cannot be captured by traditional uncoupled models.