Abstract
A method for calculation of system damping factors based on solving the general eigenvalue problem for the motion equations, given component data as the base input information, is demonstrated. The method exhibits no computational difficulties and is confirmed by comparison to approximate results based on the Method of Averaging. The method is applied to the Hermes spacecraft, a configuration that consists of a central rigid body, two flexible solar array substructures, a momentum wheel, and a liquid-mercury damping device. The synthesized modal damping values for the structural modes vary relative to those measured in orbit by factors ranging from 0 to 5.
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