Aeroelastic analysis of a sandwich panel with partially treated magneto-rheological fluid core

Abstract

This study considers the aeroelastic instability of a partially treated magneto-rheological fluid sandwich panel in supersonic airflow. The linear first-order piston theory is used for modeling the aerodynamic pressure. Using classical Hamilton’s principle along with the finite element method, the equations of motion are derived. The critical value of the non-dimensional aerodynamic pressure is obtained by traditional p-method scheme. The validity of the finite element formulation is examined through comparison with those obtained from the assumed mode formulation and the available results in the literature. Various parametric studies including the effects of applied magnetic field, core and constraining layer thicknesses are examined for several configurations of the core at simply-supported and clamped–clamped boundary conditions. The results show that the critical non-dimensional aerodynamic pressure of the sandwich panel is influenced not only by the magnetic field strength, core and constraining layer thicknesses but also strongly by the configuration of the core.