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.<>
Optimal guidance for acceleration constrained missile and maneuvering target
IEEE Transactions on Aerospace and Electronic Systems ; 26 , 4 ; 618-624
1990-07-01
370712 byte
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Exponential Criterion-Based Guidance Law for Acceleration Constrained Missile and Maneuvering Target
Online Contents | 1996
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