Abstract
Abstract : A method for the design of feedback control to limit cross-range dispersion of spinning missiles is described. The missile transverse velocity in the cross plane is selected as the cost function, and optimal linear feedbacks are derived that minimize this velocity in the presence of aerodynamic disturbances that cause lift nonaveraging. A closed-form solution is obtained for the open- and closed-loop missile response to simple disturbance moments. Cross-range dispersion control complements control of range error by angle-of-attack control of drag. The resulting two-loop system can control major sources of missile dispersion. (Author)
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