柔性多体航天器动力学

DYNAMICS OF FLEXIBLE MULTIBODY SPACECRAFTS

On the background of flexible multibody spacecrafts, the general dynamic equations of motion of flexible multibody systems with nonrooted tree topologies are obtained by using Jouradin's principle. The large displacements between contigous bodies are described through independent relative joint coordinates, and the small deformation of bodies through modal coordinates from consistent mass finite element method and vibrational normal modal analysis. The result is a set of coupled dynamic equations consisting of orbital dynamic equations, attitude dynamic equations and vibrational equations. It is compatible with equations of rigid multibody systems because of using the concepts, such as path matrix, incidence matrix, instantaneous augmented body. Findlly, the simulation results of two bodies and three bodies simple spacecrafts including a main rigid body are presented.