Problem of precision missile guidance: LQR and H‡ control frameworks

Savkin, Andrey, Pathirana, Pubudu and Faruqi, Farhan 2003, Problem of precision missile guidance: LQR and H‡ control frameworks, IEEE transactions on aerospace and electronic systems, vol. 39, no. 3, pp. 901-910.

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Title Problem of precision missile guidance: LQR and H‡ control frameworks
Author(s) Savkin, Andrey
Pathirana, PubuduORCID iD for Pathirana, Pubudu
Faruqi, Farhan
Journal name IEEE transactions on aerospace and electronic systems
Volume number 39
Issue number 3
Start page 901
End page 910
Publisher Institute of Electrical and Electronics Engineers (IEEE)
Place of publication Piscataway, N.J.
Publication date 2003-07
ISSN 0018-9251
Keyword(s) attitude control
control system analysis
missile guidance
state feedback
Summary 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 H∞ 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.
Language eng
Field of Research 090108 Satellite, Space Vehicle and Missile Design and Testing
HERDC Research category C1 Refereed article in a scholarly journal
Copyright notice ©2003, IEEE
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