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http://dx.doi.org/10.5139/IJASS.2011.12.4.365

Missile Autopilot Design for Agile Turn Control During Boost-Phase  

Ryu, Sun-Mee (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology)
Won, Dae-Yeon (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology)
Lee, Chang-Hun (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology)
Tahk, Min-Jea (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology)
Publication Information
International Journal of Aeronautical and Space Sciences / v.12, no.4, 2011 , pp. 365-370 More about this Journal
Abstract
This paper presents the air-to-air missile autopilot design for a $180^{\circ}$ heading reversal maneuver during boost-phase. The missile's dynamics are linearized at a set of operating points for which angle of attack controllers are designed to cover an extended flight envelope. Then, angle of attack controllers are designed for this set of points, utilizing a pole-placement approach. The controllers' gains in the proposed configuration are computed from aerodynamic coefficients and design parameters in order to satisfy designer-chosen criteria. These design parameters are the closed-loop frequency, damping ratio, and time constant; these represent the characteristics of the control system. To cope with highly nonlinear and rapidly time varying dynamics during boost-phase, the global gain-scheduled controller is obtained by interpolating the controllers' gains over variations of the angle of attack, Mach number, and center of gravity. Simulation results show that the proposed autopilot design provides satisfactory performance and possesses good [ed: or "sufficient" or "excellent"] capabilities.
Keywords
Missile autopilot; Agile turn; Pole pacement approach; Gain scheduling method;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
Times Cited By SCOPUS : 0
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