Tunable Flutter Resistance of Auxetic–Nanocomposite Higher‐Order Sandwich Plates Resting on a Novel Modified Kerr Foundations

Abstract

ABSTRACT High‐performance sandwich plates featuring tunable auxetic metamaterial (TAM) cores and multifunctional nanocomposite face sheets have emerged as promising components for next‐generation aerospace, energy, and precision engineering structures where lightweight design and dynamic stability are critical. This study examines the free vibration and dynamic instability of a three‐layered rectangular sandwich plate featuring a TAM core and three‐phase nanocomposite face sheets, supported by a modified Kerr‐type elastic foundation (MKTEF). The governing equations are formulated using the sinusoidal shear deformation theory (SSDT) and Hamilton's principle. They are numerically solved employing the generalized differential quadrature method (GDQM), which guarantees high computational efficiency and precision. The proposed model uniquely integrates the adverse effects of the negative Poisson's ratio in the TAM core, the interphase–fiber load transfer mechanisms within the nanocomposite layers, and the multi‐parameter interactions of the foundation, thereby offering a comprehensive framework for flutter prediction. Parametric results show that increasing the thickness of the auxetic core and the efficiency of the nanocomposite parameters greatly delays the onset of flutter. The MKTEF's shear stiffness is the most important factor in keeping it stable, while too much coupling stiffness makes it unstable too soon. Additionally, increasing the fiber and interphase contents and optimizing the auxetic geometry can boost frequency retention by as much as 20%. The results offer important tips for making better sandwich systems that can better control vibrations and resist flutter better.