A Method for Design of Feedback Control To Limit Missile Dispersion

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 openand 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 limit major sources of missile dispersion.