Abstract: The numerical model for the liquid filled coupling dynamics of spacecraft is established based on the arbitrary Lagrangian Eulerian finite element (ALE) method. The coupling effect is realized by exerting inertia forces to the liquid and sloshing forces and moments to the rigid body. The staggered algorithm is adopted to solve the liquid sloshing module and the rigid body module in an iterative way. Parts of the results of the numerical simulations are compared with those in literatures, and the proposed methods in this dissertation are proved to be applicable and accurate. The soft spring nonlinear characteristics during the lateral oscillation of the tank and the high order mode of the liquid are observed in the numerical simulations successfully. The influences of the liquid sloshing on the coupling system are analyzed.

Key words: Coupling dynamics, Liquid filled spacecraft, Large amplitude liquid sloshing, Finite element method, Spherical tank