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Missile Autopilot Design for Agile Turn Control During Boost-Phase
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 Title & Authors
Missile Autopilot Design for Agile Turn Control During Boost-Phase
Ryu, Sun-Mee; Won, Dae-Yeon; Lee, Chang-Hun; Tahk, Min-Jea;
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This paper presents the air-to-air missile autopilot design for a 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.
Missile autopilot;Agile turn;Pole pacement approach;Gain scheduling method;
 Cited by
Constrained-Optimal Based Loop-Shaping State Feedback Approach for Missile Autopilot Design, International Journal of Modeling and Optimization, 2016, 6, 3, 128  crossref(new windwow)
Robust H∞ autopilot design for agile missile with time-varying parameters, IEEE Transactions on Aerospace and Electronic Systems, 2014, 50, 4, 3082  crossref(new windwow)
Terminal Velocity Maximization of Air-to-Air Missiles in Agile Turn Phase, MATEC Web of Conferences, 2016, 77, 07009  crossref(new windwow)
Innocenti, M. (2001). Nonlinear guidance techniques for agile missiles. Control Engineering Practice, 9, 1131-1144. crossref(new window)

Lawrence, D. A. and Rugh, W. J. (1993). Gain scheduling dynamic linear controllers for a nonlinear plant. Proceedings of the 32nd IEEE Conference on Decision and Control, San Antonio, TX. pp. 1024-1029.

Lee, C. H., Kim, T. H., and Tahk, M. J. (2009). Design of missile autopilot for agile turn using nonlinear control. Proceeding of the Korean Socieyt for Aeronautical & Space Sciences Conference, Korea. pp. 667-670.

Mehrabian, A. R. and Roshanian, J. (2006). Design of gainscheduled autopilot for a highly-agile missile. Proceedings of the 1st International Symposium on Systems and Control in Aerospace and Astronautics, Harbin, China. pp. 144-149

Menon, P. K. and Yousefpor, M. (1996). Design on nonlinear autopilots for high angle of attack missiles. Proceedings of the AIAA Guidance, Navigation, and Control Conference, San Diego, CA. pp. 29-31.

Thukral, A. and Innocenti, M. (1998). A sliding mode missile pitch autopilot synthesis for high angle of attack maneuvering. IEEE Transactions on Control Systems Technology, 6, 359-371. crossref(new window)

White, D. P., Wozniak, J. G., and Lawrence, D. A. (1994). Missile autopilot design using a gain scheduling technique. Proceedings of the 26th Southeastern Symposium on System Theory, Athens, OH. pp. 606-610.

Wise, K. A. and Broy, D. J. (1998). Agile missile dynamics and control. Journal of Guidance, Control, and Dynamics, 21, 441-449. crossref(new window)

Zarchan, P. (2007). Tactical and Strategic Missile Guidance, 5th ed. Progress in Astronautics and Aeronautics, Vol. 219. Reston: American Institute of Aeronautics and Astronautics.

Zipfel, P. H. (2000). Modeling and Simulation of Aerospace Vehicle Dynamics. Reston: American Institute of Aeronautics and Astronautics.