Abstract
In this paper a rigid missile (booster) guidance and control system is synthesized by means of an advanced control optimization technique called the Parametric Expansion Method. It was developed by Dr. Charles W. Merriam III of the General Electric Research Laboratory, Schenectady, N. Y. The results obtained are evaluated in a digital simulation of the missile dynamics and compared with those obtained using a similar system which was synthesized by the more conventional means of root locus.
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