Modeling, analysis, and control of MFC sandwiched laminate panel flutter with general layups and arbitrary boundary conditions

摘要: Abstract In this paper, a new solution approach based on Lagrange multipliers is developed for aeroelastic panel flutter analysis of rectangular composite plates sandwiched by two Macro Fiber Composites (MFCs). The smart has general stacking sequences and subjected to the elastic edge restraints. By utilizing assumed mode technique, displacements electric potentials are expanded using formerly determined shapes. Afterward, potential kinetic energies problem achieved employing equation, discretized equations motion obtained. supersonic aerodynamic load modeled through well-known piston theory included within means non-conservative force term equation. Deriving more simplified thanks orthogonality Legendre polynomials. Finally, input voltage MFC actuator proportional or velocity feedback control algorithms sensor output. capability credibility proposed confirmed comparing results with those FEM. method used investigate effects MFCs orientations boundaries plates.