نویسندگان

دانشکدة مهندسی برق و الکترونیک، دانشگاه صنعتی شیراز، شیراز، ایران

چکیده

در این مقاله، رویکردی جدید در طراحی قانون هدایت موشک به‌منظور برخورد با اهداف دارای قابلیتهای مانوری بالا ارائه میشود. رویکرد مطرح شده براساس تلفیق تئوری‌های پایداری زمان محدود و پایداری جزئی (پایداری جزئی زمان محدود) است. همچنین تطابق فیزیکی رویکرد مطرح شده با یک سناریوی هدایت موفق که به برخورد منجر می‌شود، نشان داده شده است. در روند طراحی، بردار شتاب هدف به‌عنوان ورودی اغتشاشی درنظر گرفته می‌شود و تنها باند بالای آن در طراحی قانون هدایت باید معلوم باشد. بنابراین، مانور هدف به هیچ فرم مشخص و از پیش ‌تعیین‌شدهای محدود نشده و  اندازه‌گیری یا تخمین بردار شتاب هدف در حینمانور لازم نیست. کارایی قانون هدایت طراحی شده، هم به لحاظ تئوری و هم توسط شبیهسازی نشان داده شده است.

کلیدواژه‌ها

عنوان مقاله [English]

New Approach in Guidance Law Design Based on Finite-Time Partial Stability Theorem

نویسندگان [English]

  • Tahere Binazadeh
  • Mohammad Hossein Shafiei
  • Elham Bazregarzadeh

Faculty of Electrical and Electronic Engineering, Shiraz University of Technology, Shiraz, Iran

چکیده [English]

This paper presents a novel approach in design of missile guidance law against highly maneuvering targets. This approach is based on the principles of partial stability and finite-time stability (finite-time partial stability). Also, it is shown that the designed guidance law is in conformity with a real guidance scenario that leads to collision. In the design procedure the acceleration vector of the target is assumed as an external bounded disturbance and only this bound is required in the design of the guidance law. Therefore, the maneuver of the target is not restricted to any known and predetermined structure and measurement or estimation of the target acceleration vector during the maneuver is not necessary. The performance of the proposed guidance law is shown through analysis and computer simulations.

کلیدواژه‌ها [English]

  • Finite-time stabilization
  • Partial stability
  • Guidance law
 
[1] Guelman, M., “The Closed Form Solution of True Oportional Navigation,” IEEE Transactions on Aerospace and Electronic Systems, Vol. 12,  No. 4, 1979, pp. 472-482.
[2] Mohammadzaman, E. and Momeni, H.R, “Short Time Stability Approach to Guidance Law Design,” Journal of Space Science and Technology (JSST), Iranian Aerospace Society, Vol. 3, No. 1-2, 2010, pp. 37-44 (In Persian).
[3] Yuan, P. J. and Chern, J. S., “Ideal Proportional Navigation,” Journal of Guidance, Control, and Dy-Namics, Vol. 15, No. 5, 1992, pp. 1161-1166.
[4] Pourtakdoust, S. H., Fakhri, M. and Assadian, N., “Development of an Integrated Design Environment for Optimal Ascent Trajectory Planning,” Journal of Space Science and Technology (JSST), Vol. 1, No. 1, 2008, pp.1-10 (In Persian).
[5] Oshman, Y. and Arad, D., “Differential Game Based Guidance Law Using Target Orientation Observations,”IEEE Transaction on Aerospace and Electronic Systems, Vol. 42, No. 1, 2009, pp. 316-326.
[6] Shaferman, V. and Shima, T., “Linear Quadratic Guidance Laws for Imposing a Terminal Intercept Angle,” Journal of Guidance, Control, and Dynamics, Vol. 31, No. 5, 2008, pp.1400-1412.
[7] Lechevin, N. and Rabbath, CA., “Lyapunov-Based Nonlinear Missile Guidance,” Journal of Guidance, Control and Dynamics, Vol. 27, No. 6, 2004, pp.1096–102.
[8] Ryoo, C. K, Kim, Y. H, Tahk, M. J, and Choi, K., “A Missile Guidance Law Based on Sontag’s Formula to Intercept Maneuvering Targets,” International Journal of Control, Automation, and Systems, Vol. 5, No. 4, 2007, pp. 397–409.
[9] Shieh, C. S., “Nonlinear Rule–Based Controller for Missile Terminal Guidance,” IEEE Proceedings Control Theory Application, Vol. 150, No. 1, 2004, pp. 45–48.
[10]Zhou, D., Mu, C. and Xu, W., “Adapt Sliding-Mode Guidance of a Homing Missile,” Journal of Guidance, Control, and Dynamics, Vol. 22, No. 4, 1999, pp. 589–594.
[11] Iaw, D. C., Liang, Y. W. and Cheng, C. C., “Nonlinear Control for Missile Terminal Guidance,” Journal of Dynamics Systems, Measurement, and Control, Vol. 122,No. 4, 2000, pp. 663–668.
[12] Brierly, S. D. and Long, C. R., “Application of Sliding Mode Control to Air–Air Interception Problem,” IEEE Transactionson Aerospace and Electronic Systems, Vol.26, No. 2, 1990, pp. 306–25.
[13]Idan, M, Shima, T. and Golan, O. M., “Integrated Sliding Mode Autopilot-Guidance for Dual Control Missiles,” AIAA Guidance, Navigation, and Control Conference and Exhibit, 2005.
[14]Tang, C. D., Chen, H. Y., “Nonlinear H∞ Robust Guidance Law for Homing Missiles,” Journal of Guidance, Control and Dynamics, Vol. 21, No. 6, 1998,pp. 882–890.
[15]Chen, B. S., Chen, Y. Y.and Lin, C. L., “Nonlinear Fuzzy H∞ Guidance Law with Saturation of Actuators Against Maneuvering Targets,” IEEE Transactions on Control System Technology, Vol. 10, No. 6, 2002, pp.769–779.
[16] Shafie, H. and Binazadeh, T., “Partial Stability-Based Guidance,” ISA Transactions, Vol. 51, 2012, pp. 141-145.
[17] Bhat, S. P. and Bernstein, D. S., “Finite –Time Stability of Continuous Autonomous Systems,” SIAM Journal of Control and Optimization, Vol. 38, No. 3, 2000, pp. 751