Abstract
For homing missile weapon systems, integrated design of guidance and control using backstepping control with disturbance observer are studied. New guidance strategy with transversal velocity in LOS frame and Time to Go (tgo) is devised. The stability of integrated backstepping guidance and control logic is proven by Lyapunov sense. Tracking performance is also considered. The deflection command is a function of linear aerodynamic coefficients and measurable states. The designed guidance-control system performance is verified via numerical simulation.
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