We present a method for numerical simulations of maneuvering aircraft, which uses first-order unsteady panel as the only source aerodynamic forces and moments. By using proposed method, it is possible to simulate motion an while required inputs are geometry inertia characteristics, significantly reduces time start simulation. validated by comparison recordings flight parameters (position, veloc...

in this paper deflection and free vibration of sandwich panel is studied. the core of sandwich panels is made of hexagonal honeycomb and faces are made of two different materials of carbon fiber reinforced plastic and k-aryl/epoxy covering. the governing equations are deduced from the first order sheer deformation theory (fsdt) and they are solved using generalized differential quadrature metho...

in this paper, the behavior of free vibrations and buckling of the sandwich panel with a flexible core was investigated using a new improved ‎high-order sandwich panel theory. in this theory, equations of motion were formulated based on shear stresses in the core. first-order shear deformation theory was ‎applied for the procedures. in this theory, for the first time, incompatibility problem of...