The coupling dynamics study of spacial flexible structures that takes the coupling efforts into account is of great importance in aerospace field. The flexible structures were discretized by means of finite element method(FEM), and modal matrix of the flexible structures was obtained. The dynamical model of rigid-flexible hybrids in large overall motions was established based on the theory of modal superposition method and Kane equations. And then, the equations were solved througth Matlab programming. The validity of dynamical model and Matlab programming was verified by comparision of the results of Matlab simulation and business-software simulation. This research solves dynamical simulation of the spacecraft composed of rigid central body and flexible appendages.
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