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THE design of modern flight vehicles requires sophisticated mathematical models. Aeroservoelastic models combine aerodynamics, controls, and structural models into a single model that can be used for control law design. The importance of performing active control for flutter suppression, gust load alleviation, and ride quality enhancement was identified during the NASA High-Speed Research Program [1, 2]. The design of control laws for this class of vehicles continues [3]. Ultimately, state-space models are required. The size of such aeroservoelastic models can be quite large (on the order of thousands of states [4]) and thus unsuitable for control law design. One approach for reduction is computation of a balanced realization followed by truncation of the least important states. The balanced realization applied in the present research involves computing the controllability and observability Gramians of the …