کنترل تطبیقی بهینه وضعیت ماهواره در حضور عدم قطعیت در اینرسی با استفاده از پارامترهای مارکوف

نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 دانشکده مهندسی فناوری های نوین، دانشگاه شهید بهشتی ، تهران، ایران

2 دانشکده فناوری های نوین، دانشگاه شهید بهشتی، تهران ایران

10.30699/jsst.2021.1199

چکیده

همواره در طی مأموریت‌های فضایی عدم قطعیت‌ در مسئله کنترل وضعیت ماهواره‌ها وجود دارد. از این رو کنترل تطبیقی روشی است که مورد توجه قرار می‌گیرد. از جمله مشکلات کنترل تطبیقی متداول حجم محاسباتی بالا و نبود روش تئوری عمومی برای طراحی مکانیزم تطبیق می‌باشد. در این مقاله یک روش کنترلی بر اساس مفاهیم تطبیقی و بهینه با استفاده از پارامترهای مارکوف جهت کنترل سرعت زاویه‌ای و وضعیت ماهواره معرفی می‌شود. این روش دارای قابلیت دنباله‌روی فرمان است، و بر اساس گروه متعامد خاص از مرتبه سه گسترش می‌یابد و مشکل سینگولاریتی ندارد. همچنین جهت مقایسه این روش با دیگر روش‌های کنترلی، روش کنترلی بهینه تنظیم‌کننده مربعی خطی (LQR) نیز شبیه‌سازی می‌گردد. در نهایت نتایج حاصل از شبیه‌سازی‌ها بیانگر این است که عملکرد روش کنترلی تطبیقی ارائه شده بهینه است، و همچنین این روش نسبت به عدم قطعیت در اینرسی مقاوم می‌باشد.

کلیدواژه‌ها


عنوان مقاله [English]

Optimal Adaptive Control of Satellite Attitude in Presence of Uncertainty in Moment of Inertia Using Markov Parameters

نویسندگان [English]

  • Mohammad Navabi 1
  • Nazanin Safaei 2
1 Faculty of New Technologies Engineering, Shahid Beheshti University, Tehran, Iran
2 Faculty of New Technologies Engineering, Shahid Beheshti University, Tehran, Iran
چکیده [English]

Several novel control techniques have been created as a result of the diversity of researches which are conducted about the problem of satellite attitude control. There are always uncertainties in the problem of satellite attitude control in the space missions. Therefore, Adaptive control is a method which is taken into consideration. High computational volume is one of the problems of adaptive control technique. In this paper, a control technique which is based on optimization concepts is introduced for the problem of satellite angular velocity and attitude control. Also, it's developed based on the three-dimensional special orthogonal group, and it's not faced by a singularity problem. For comparison, the linear quadratic regulator (LQR) control technique is simulated. Finally, the results of the simulations show that the performance of the presented adaptive control technique is optimal, and this method is robust to inertia changes.

کلیدواژه‌ها [English]

  • Satellite attitude control
  • Adaptive control
  • Recursive least squares
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