Optimal Guidance for Acceleration Constrained Missile and Maneuvering Target

Abstract

Excplicit formulas of optimal guidance law for acceleration constrained arbitrary order missile and maneuvering target are derived. These formulas are given in terms of the missile's transfer function and acceleration constraint, and the transfer function/shaping filter of the target. Optimal, full state feedback guidance law is synthesized against a target performing a barrel roll maneuver, and compared to the performance of the Proportional Navigation for minimum and non-minimum missile. Simulation of a 3rd order missile show the relative gain from using the full order guidance law for several acceleration constraints.