Optimal guidance laws for brunovsky form systems

In this paper we present a different approach to solve the general optimal guidance laws problem and derive an analytic closed from solution to it. Based on that optimal guidance law for Brunovský form systems, closed form expressions suitable for any controller type (e.g. missile acceleration, jerk and etc) and any set of plant equations, are derived. Particularly, we derive from the general closed form structure five guidance laws and compare between them in terms normalized quantities of the required missile acceleration and jerk as a function of the target maneuver (jerk step or acceleration step) and missile heading error.