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Optimal guidance for acceleration constrained missile and maneuvering target

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2 Author(s)
I. Rusnak ; RAFAEL, Haifa, Israel ; L. Meir

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 proportional navigation (PN) for minimum and nonminimum phase missile. Simulation of a third-order missile shows the relative gain from using the full-order guidance law

Published in:

IEEE Transactions on Aerospace and Electronic Systems  (Volume:26 ,  Issue: 4 )