نوع مقاله : علمی- ترویجی

نویسندگان

1 دانشجوی کارشناسی ارشد، گروه مهندسی برق، دانشکده مهندسی، دانشگاه خلیج فارس، بوشهر، ایران

2 استادیار، گروه مهندسی برق، دانشکده مهندسی ، دانشگاه خلیج فارس، بوشهر ، ایران

چکیده

در این مقاله، با در نظر گرفتن دینامیک عملگر به طراحی قانون هدایت در یک مسئلة هدایت دو بعدی پرداخته شده است. برای دستیابی به این هدف، با استفاده از رویکرد گام به عقب، روش هدایت تناسبی به‌گونه‌ای تغییر داده شده تا پایداری سیستم حلقة بسته با وجود دینامیک عملگر تضمین شود. از این‌رو، سعی بر آن است که عملکرد حلقة هدایت (برای مثال مشخصات پاسخ گذرا و فاصله از دست‌دهی) با الگوریتم هدایت پیشنهادی در مقایسه با قانون هدایت تناسبی تا حد امکان بهبود داده شود. برای این منظور، با به‌کارگیری ایدة گام به عقب و نظریة پایداری لیاپانف، قانون هدایت کلاسیک به‌گونه‌ای اصلاح خواهد شد تا حلقة هدایت در حضور دینامیک عملگر پایدار مجانبی شود. الگوریتم هدایت پیشنهادی در یک مسئله هدایت نوعی شبیه‌سازی می‌شود. نتایج به دست آمده کارآیی الگوریتم هدایت اصلاح شده را در مقایسه با قانون هدایت تناسبی نشان می‌دهد.

کلیدواژه‌ها

عنوان مقاله [English]

Improved Guidance Law Design in Presence of Actuator Dynamic via Back-stepping Approach

نویسندگان [English]

  • Ali Yousefpour 1
  • Valiollah Ghaffari 2

1 M.Sc. Student Department of Electrica Engineering School of Engineering, Persian Gulf University, Bushehr.Iran

2 Assistant Professor, Department of Electrical Engineering, School of Engineering, Persian Gulf University, Bushrhr.Iran

چکیده [English]

This paper concerns on guidance law design by considering of the actuator effect. For achieving this goal, the proportional guidance (PN) method would be modified via the back-stepping approach such that the closed-loop stability is guaranteed in the presence of the actuator dynamic. Thus, it is interested to improve the guidance system performance (for example the transient response characteristic and miss-distance error) by the proposed guidance algorithm. Hence, the PN guidance law would be corrected such that the closed-loop system is asymptotically stabilized. The suggested algorithm is numerically simulated in a typical guidance problem. The simulation results verify the effectiveness of the redesigned guidance technique in comparison with the PN method. 

کلیدواژه‌ها [English]

  • Proportional Navigation
  • Miss-distanceerror
  • Actuator Dynamic
  • Back-stepping Approach
[1] Zarchan, P., Tactical and Strategic Missile Guidance, American Institute of Aeronautics and Astronautics, Reston, USA, 2012.
[2] Siouris, G.M. Missile Guidance and Control Systems, Springer Science & Business Media, BerlinGermany, 2004.
[3] Yanushevsky, R. and Boord, W., "Lyapunov Approach to Guidance Laws Design", Non-linear Analysis: Theory, Methods & Applications, Vol. 63, No's. 5-7, pp. 743-749, 2005.
[4] Saleem, A. and Ratnoo. A., "Lyapunov-based Guidance Law for Impact Ttime Control and Simultaneous Arrival", Journal of Guidance, Control, and Dynamics, Vol. 39, No. 1, pp. 164-173, 2016.
[5] Shima, T., Idan, M., and Golan, O.M., "Sliding-mode Control for Integrated Missile Autopilot Guidance", Journal of Guidance, Control, and Dynamics, Vol. 29, No. 2, pp. 250-260, 2006.
[6] Moosapour, S.H., Bagherzadeh, M., Alizadeh, G., and Ghaemi, S., ''Back-stepping Guidance Law Design for Missile Against Maneuvering Targets", International Conference on Control, Instrumentation and Automation, Shiraz, Iran, 2011.
[7] Behnamgol, V., Vali, A., and Mohammadi, A., "A New Back-stepping Sliding Mode Guidance Law Considering Control Loop Dynamics", Journal of Space Science and Technology,Vol. 89, No. 4, pp. 9-16, 2016.
[8] Gutman, S., "On Optimal Guidance for Homing Missiles",  Journal of Guidance and Control, Vol. 2, No. 4, pp. 296-300, 1979.
[9] Yang, C.-D. and Chen, H.-Y., "Non-linear H Robust Guidance Law for Homing Missiles", Journal of Guidance, Control, and Dynamics, Vol. 21, No. 6, pp. 882-890, 1998.
[10] Zhou, D., Sun, S., and Teo, K.L., "Guidance Laws with Finite Time Convergence", Journal of Guidance, Control, and Dynamics, Vol. 32, No. 6, pp. 1838-1846, 2009.
[11] Behnam Gol, V., Zaman, I.M., Vali, A.R., and Ghahramani, N.A., "Guidance Law Design, Using Finite Time Second Order Sliding Mode Control",  Journal of Control, Vol. 5, No. 3, pp. 36-44, 2011.
[12] Dimirovski, G.M., Deskovski, S.M., and Gacovski, Z.M.,  "Classical and Fuzzy-system Guidance Laws in Homing Missiles Systems", IEEE Aerospace Conference Proceedings, Vol. 5, pp. 3032-3047, 2004.
[13] Lin, C.-M. and Hsu, C.-F. "Guidance Law Design by Adaptive Fuzzy Sliding-mode Control",  Journal of Guidance, Control, and Dynamics, Vol. 25, No. 2, pp. 248-256, 2002.
[14] Breivik, M., and Fossen, T.I.  "Principles of Guidance-based Path Following in 2D and 3D", The 44th IEEE Conference on Decision and Control, Seville, Spain, 2005.
[15] Palumbo, N.F., Blauwkamp, R.A., and Lloyd, J.M., "Basic Principles of Homing Guidance", Johns Hopkins APL Technical Digest, Vol. 29, No. 1, pp. 25-41, 2010.
[16] Ghaffari, V., "Guidance Algorithm Selection Based on Line-of-sight Angleinguidance Systems", High Speed Craft, Vol. 16, No. 61, pp.50-57, 2018.
[17] Cho, N. and Kim, Y., "Modified Pure Proportional Navigation Guidance Law for Impact Time Control", Journal of Guidance, Control, and Dynamics, Vol.  39, No. 4, pp. 852-872, 2016.
[18] Jeon, In-Soo, and Jin-Ik Lee. "Impact-time-control Guidance Law with Constraints on Seeker Look Angle", IEEE Transactions on Aerospace and Electronic Systems, Vol. 53, No. 5, pp. 2621-2627, 2017.
[19] Song, J., Song, S., and Xu, S., "Three-dimensional Cooperative Guidance Law for Multiple Missiles with Finite-time Convergence",  Aerospace Science and Technology, Vol. 67, 193-205, 2017.
[20] Song, J., and Song. S.,"Three-dimensional Guidance Law Based on Adaptive Integral Sliding Mode Control", Chinese Journal of Aeronautics, Vol. 29, No. 1, pp. 202-214, 2016.