Discrete Advanced Guidance for High Order Acceleration Constrained Missile and Maneuvering Target

Abstract

An explicit, closed form formula of discrete advanced guidance law for a linear, time-invariant, high-order and acceleration-constrained missile and a linear, time-invariant arbitrary-order, maneuvering target is derived. The formula is given in terms of the missile's transfer function and acceleration constraint, the shaping filter of the target and responses to initial conditions. Optimal full state feedback guidance law is synthesized and compared to a first order approximation for minimum and non-minimum phase missile. Simulation of a third order missile model shows the relative gain from using the full state guidance law for several values of the missile time response and acceleration constraint.