JOURNAL BROWSE
Search
Advanced SearchSearch Tips
Missile Autopilot Design for Agile Turn Using Time Delay Control with Nonlinear Observer
facebook(new window)  Pirnt(new window) E-mail(new window) Excel Download
 Title & Authors
Missile Autopilot Design for Agile Turn Using Time Delay Control with Nonlinear Observer
Lee, Chang-Hun; Kim, Tae-Hun; Tahk, Min-Jea;
  PDF(new window)
 Abstract
This paper deals with missile autopilot design for agile turn phase in air-to-air engagement scenarios. To attain a fast response, angle-of-attack (AOA) is adopted for an autopilot command structure. Since a high operational AOA is generally required during the agile turn phase, dealing with the aerodynamic uncertainties can be a challenge for autopilot design. As a remedy, a new controller design method based on robust nonlinear control methodology such as time delay control is proposed in this paper. Nonlinear observer is also proposed to estimate the AOA in the presence of the model uncertainties. The performance of the proposed controller with variation of the aerodynamic coefficients is investigated through numerical simulations.
 Keywords
High angle-of-attack;Agile turn;Missile autopilot;Nonlinear control;Time delay control;
 Language
English
 Cited by
1.
Missile Autopilot Design for Agile Turn Control During Boost-Phase,;;;;

International Journal of Aeronautical and Space Sciences, 2011. vol.12. 4, pp.365-370 crossref(new window)
2.
Missile Autopilot Design for Agile Turn Using Time Delay Control with Nonlinear Observer,;;;

International Journal of Aeronautical and Space Sciences, 2011. vol.12. 3, pp.266-273 crossref(new window)
3.
An auto weather-vaning system for a DP vessel that uses a nonlinear controller and a disturbance observer,;;

International Journal of Naval Architecture and Ocean Engineering, 2014. vol.6. 1, pp.98-118 crossref(new window)
1.
Missile two-loop acceleration autopilot design based on 𝓛1adaptive output feedback control, International Journal of Aeronautical and Space Sciences, 2014, 15, 1, 74  crossref(new windwow)
2.
A Model Matching STR Controller for High Performance Aircraft, ISRN Aerospace Engineering, 2013, 2013, 1  crossref(new windwow)
3.
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)
 References
1.
Choi, Y. S., Lee, H. C., and Choi, J. W. (2003). Autopilot design for agile missile with aerodynamic fin and side thruster. SICE 2003 Annual Conference, Fukui, Japan. pp. 1476-1481.

2.
Devaud, E., Siguerdidjane, H., and Font, S. (1998). Nonlinear dynamic autopilot design for the non minimum phase missile. Proceedings of the IEEE Conference on Decision and Control, Tampa, FL. pp. 4691-4696.

3.
Kim, K. U., Kang, S. H., Kim, H. J., Lee, C. H., and Tahk, M. J. (2010). Realtime agile-turn guidance and control for an air-to-air missile. AIAA Guidance, Navigation, and Control Conference, Toronto, Canada. pp. 29-31.

4.
Kim, Y. H., Park, J. W., Lee, C. H., and Tahk, M. J. (2009). Control input discretization and optimization method for half-turn maneuver analysis of short range air-to-air missile. Proceeding of KSAS Spring Conference, Pyeongchang, Korea. pp. 373-376.

5.
Lee, C. H., Kim, T. H., Ryu, S. M., and Tahk, M. J. (2009a). Analysis of turning maneuver for agile missile using trajectory optimization. Proceeding of KSAS Spring Conference, Pyeongchang, Korea. pp. 369-372.

6.
Lee, C. H., Kim, T. H., and Tahk, M. J. (2009b). Autopilot design for agile turn using time-delay control with observer. Proceeding of KSAS Fall Conference, Gyeongju, Korea. pp. 822-825.

7.
Lee, C. H., Kim, T. H., and Tahk, M. J. (2009c). Design of missile autopilot for agile turn using nonlinear control. Proceeding of KSAS Fall Conference, Gyeongju, Korea. pp. 667-670.

8.
Mehrabian, A. R. and Roshanian, J. (2006). Design of gain-scheduled 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.

9.
Menon, P. K. and Yousefpor, M. (1996). Design of nonlinear autopilots for high angle of attack missiles. AIAA Guidance, Navigation, and Control Conference, San Diego, CA. pp. 29-31.

10.
Ryu, S. M., Won, D. Y., Lee, C. H., and Tahk, M. J. (2010). High angle of attack missile autopilot design by pole placement approach. Proceedings of the 3rd International Symposium on Systems and Control in Aeronautics and Astronautics, Harbin, China. pp. 535-539.

11.
Slotine, J. J. E. and Li, W. (1991). Applied Nonlinear Control. Englewood Cliffs: Prentice Hall.

12.
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)

13.
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)

14.
Youcef-Toumi, K. and Wu, S. T. (1991). Input/output linearization using time delay control. Proceedings of the American Control Conference, Boston, MA. pp. 2601-2606.