Articulated and flexible multibody satellite dynamics modeling

This paper is concerned with the derivation of the equations of motion for a maneuvering flexible satellite orbiting around the Earth. The structure is assumed to undergo large rigid-body maneuvers and small elastic deformations. The mathematical model is worked out in two levels: in the first one attention is focused on the effects of the rigid dynamics on the flexible motion, while in the second one the reciprocal influence is evaluated. The satellite is provided with flexible solar arrays linked up with the main body with torsional and bending articulations: the mathematical model also considers hinges compliance, when the appendages are blocked in the desired position. Different rotational maneuvers are simulated and numerical results highlight the limitation of the first level modelization, which can be used with confidence for structural analysis, but results inadequate for flight dynamics and control applications. © 2002 by the author(s). Published by the American Institute of Aeronautics and Astronautics, Inc.