Abstract
A modal controller is designed for attitude control of a class of large flexible space structures via the Simon-Mitter pole allocation method. The sensitivity characteristics of the closed loop system is investigated when the space structure changes its vibrational features typified by the modal frequency. This investigation is based on a linear approximation of the sensitivity matrix, which does not need the closed loop eigenvectors. A primitive modeling problem for the finite element analysis and coordinate transformation procedures are also briefly described. An illustrative example of a test vehicle with two vibration modes damonstrates the validity and usefulness of the proposed design and analysis methods.
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