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<p>This article studies the supersonic flutter (aeroelastic stability) behavior of an adhesive-bonded nanocomposite conical shell. The shell consists of two parts, each made from a lightweight polymer matrix reinforced with graphene nanoplatelets (GNPs), joined by an elastic, homogeneous adhesive. The outer and inner parts may have different GNP dispersion patterns and mass fractions. Aerodynamic pressure is modeled with piston theory, and the shell is modeled using the first-order shear deformation theory (FSDT). The governing equations, boundary conditions, and compatibility conditions are derived using Hamilton’s principle. The coupled differential equations are solved analytically in the circumferential direction and approximately in the meridional direction. The effects of boundary conditions, adhesive thickness, lap joint length, and GNP dispersion pattern and mass fraction on the aeroelastic stability of the structure are investigated. Numerical results show that the natural frequencies and aeroelastic stability depend more on the dispersion pattern and mass fraction of the GNP in the inner part of the structure than in the outer part.</p>

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The Vibration Analysis of an Adhesive-Bonded GNP-Reinforced Conical Shell Subjected to Supersonic Fluid Flow

  • 期刊论文

  • 发表日期：

    2026年1月6日

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  • Hossein Amirabadi,
  • Arashk Darakhsh,
  • Masume Eskandari,
  • Hassan Afshari

摘要

This article studies the supersonic flutter (aeroelastic stability) behavior of an adhesive-bonded nanocomposite conical shell. The shell consists of two parts, each made from a lightweight polymer matrix reinforced with graphene nanoplatelets (GNPs), joined by an elastic, homogeneous adhesive. The outer and inner parts may have different GNP dispersion patterns and mass fractions. Aerodynamic pressure is modeled with piston theory, and the shell is modeled using the first-order shear deformation theory (FSDT). The governing equations, boundary conditions, and compatibility conditions are derived using Hamilton’s principle. The coupled differential equations are solved analytically in the circumferential direction and approximately in the meridional direction. The effects of boundary conditions, adhesive thickness, lap joint length, and GNP dispersion pattern and mass fraction on the aeroelastic stability of the structure are investigated. Numerical results show that the natural frequencies and aeroelastic stability depend more on the dispersion pattern and mass fraction of the GNP in the inner part of the structure than in the outer part.