LAUSR

In this paper, the precise deployment dynamical behavior is studied for a planetary rover mast mechanism of spacecraft undergoing large attitude adjustment motion. In the conventional dynamic formulation, flexible appendages of mast attached to spacecraft are taken as linear deformations with isotropic material, and it can result in improper responses. Therefore, the present model takes into account the coupling relations between geometric nonlinearity and laminated structure characteristics. Accordingly, by introducing the nonlinear constitutive relation of laminated materials based on the higher-order shear deformation theory, the nonlinear dynamic model of the planetary rover mast mechanism composed of laminated composite material is deduced based on the virtual work principle including geometric nonlinearity and material nonlinearity. By comparing the experiments results and those of present nonlinear model, the correctness and accuracy of present nonlinear model are verified. Furthermore, numerical examples are presented to investigate the nonlinear laminated material effect on deployment dynamical behavior of the planetary rover mast mechanism using different laying angles and curvature radii, and the results also testify the accuracy and efficiency of the formulation. The conclusions have important theoretical value and practical engineering significance for the dynamic characteristics and vibration control of attitude adjustment of planetary rover mast mechanism.