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A Feedback-Form of Terminal-Phase Optimal Guidance Law for BTT Missiles Considering Autopilot Dynamics
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 Title & Authors
A Feedback-Form of Terminal-Phase Optimal Guidance Law for BTT Missiles Considering Autopilot Dynamics
Yoo, Seong-Jae; Hong, Jin-Woo; Ha, In-Joong;
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 Abstract
In contrast with STT missiles, the guidance law design for BTT missiles should be based on 3-dimensional pursuit kinematics, since the pitch and roll channels of BTT missiles are coupled dynamically. More generally than the prior works, the dynamics of pitch and roll channels, as well as 3-dimensional pursuit kinematics are considered in the design of our terminal-phase optimal guidance law for BTT missiles proposed in this paper. Thereby, the proposed optimal guidance law guarantees high capturability with small miss distance without significant performance degradation due to time-lag effect even in case of relatively slow autopilot dynamics. Moreover, the resulting optimal guidance law is expressed explicitly in feedback-form with the coefficients given as the functions of time-to-go. The effectiveness and practicality of our work is demonstrated through various simulation results.
 Keywords
BTT Missile;Optimal Guidance Law;Autopilot Dynamics;3-D Pursuit Kinematics;
 Language
Korean
 Cited by
 References
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