OPTIMAL GUIDANCE FOR ACCELERATION CONSTRAINED MISSILE AND MANEUVERING TARGET

Explicit formulas of optimal guidance laws for an acceleration-constrained arbitrary-order missile and maneuvering target are derived. These formulas are given in terms of the transfer function and acceleration constraint of the missile, 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 with the performance of the proportional navigation (PN) for minimum and nonminimum phase missile. Simulation of a 3rd-order missile shows the relative gain from using the full-order guidance law. © 1990 IEEE