Numerical and experimental investigation on nonlinear dynamic behavior of satellite antenna reflector mechanism considering geometrical nonlinear effect and laminated composite material

Abstract

A nonlinear dynamic modeling method for a satellite antenna system composed of laminated composite shell reflector undergoing large rotation considering its geometrically nonlinear effect and material nonlinearity effect is proposed in this paper. The present model treats flexible appendages of a spacecraft mechanism as laminated composite material and takes into account the coupling relations between nonlinear constitutive relation of laminated material characteristics and large-angle maneuver. Then, the corresponding efficient formulations for laminated paraboloidal reflector based on higher order shear deformation theory and Hamilton's principle are developed to capture the correct dynamic response. Furthermore, the experiment for evaluating the dynamic behavior of laminated composite reflector is conducted; the vibration of the laminated composite material is smaller than that of isotropic material. Numerical results are in good agreement with those obtained from experiment to validate the correctness of the present modeling formulation. Finally, numerical simulations demonstrate that nonlinear stiffness terms and elastic force resulting from with different curvature and different laying angle have significant effect on the dynamic characteristics. The larger curvature of the reflector and the larger laying angle of the laminated composite material will induce the larger deformation of the reflector. The conclusion has important theoretical value and practical significance for the study of controlling the pointing behavior of satellite antennas.