Supersonic flutter suppression of electrorheological fluid-based adaptive panels resting on elastic foundations using sliding mode control

• Published in: Smart materials and structures Vol. 21; no. 4; pp. 45005 - 1-16
• Main Authors: Hasheminejad, Seyyed M, Nezami, M, Aryaee Panah, M E
• Format: Journal Article
• Language: English
• Published: Bristol IOP Publishing 01.04.2012; Institute of Physics
• Subjects: Active control; Electrorheological fluids; Exact sciences and technology; Foundations; Fundamental areas of phenomenology (including applications); Galerkin methods; General equipment and techniques; Instruments, apparatus, components and techniques common to several branches of physics and astronomy; Mathematical models; Physics; Runge-Kutta method; Servo and control equipment; robots; Sliding mode control; Solid mechanics; Structural and continuum mechanics; Supersonic flutter; Vibration, mechanical wave, dynamic stability (aeroelasticity, vibration control...); Supersonic flow; Equation of motion; Sliding mode; Sandwich structure; Control synthesis; Aerodynamics; State space method; Boundary condition; Fourier series; Adaptive method; Time domain method; Active system; Electrorheological fluid; Kelvin voigt model; Vibration control; Flutter; Galerkin method; Eigenvalue problem; Aeroelasticity; Elastic foundations
• ISSN: 0964-1726; 1361-665X
• DOI: 10.1088/0964-1726/21/4/045005

Brief reviews on suppressing panel flutter vibrations by various active control strategies as well as utilization tunable electrorheological fluids (ERFs) for vibration control of structural systems are presented. Active suppression of the supersonic flutter motion of a simply supported sandwich panel with a tunable ERF interlayer, and coupled to an elastic foundation, is subsequently investigated. The structural formulation is based on the classical beam theory along with the Winkler-Pasternak foundation model, the ER fluid core is modeled as a first-order Kelvin-Voigt material, and the quasi-steady first-order supersonic piston theory is employed to describe the aerodynamic loading. Hamilton's principle is used to derive a set of fully coupled dynamic equations of motion. The generalized Fourier expansions in conjunction with the Galerkin method are then employed to formulate the governing equations in the state space domain. The critical dynamic pressures at which unstable panel oscillations (coalescence of eigenvalues) occur are obtained via the p-method for selected applied electric field strengths (E = 0,2,4 kV mm−1). The classical Runge-Kutta time integration algorithm is subsequently used to calculate the open-loop aeroelastic response of the system in various basic loading configurations (i.e. uniformly distributed blast, gust, sonic boom, and step loads), with or without an interacting soft/stiff elastic foundation. Finally, a sliding mode control synthesis (SMC) involving the first six natural modes of the structural system is set up to actively suppress the closed-loop system response in supersonic flight conditions and under the imposed excitations. Simulation results demonstrate performance, effectiveness, and insensitivity with respect to the spillover of the proposed SMC-based control system. Limiting cases are considered and good agreements with the data available in the literature as well as with the computations made by using the Rayleigh-Ritz approach are obtained.