Addressed here is the precision missile guidance problem where the successful intercept criterion has been defined in terms of both minimizing the miss distance and controlling the missile body attitude with respect to the target at the terminal point. We show that the Hinfinity control theory, when suitably modified, provides an effective framework for the precision missile guidance problem. The existence of feedback controllers (guidance laws) is investigated for the case of finite horizon and non-zero initial conditions. Both state feedback and output feedback implementations are explored.
Problem of precision missile guidance: LQR and Hinfinity control frameworks
IEEE Transactions on Aerospace and Electronic Systems ; 39 , 3 ; 901-910
2003
10 Seiten, 16 Quellen
Aufsatz (Zeitschrift)
Englisch
Problem of Precision Missile Guidance: LQR and H(infinity) Control Frameworks
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