نوع مقاله : علمی پژوهشی

نویسندگان

1 استادیار، پژوهشکده رانشگرهای فضایی، پژوهشگاه فضایی ایران، تبریز، ایران

2 پژوهشگر، پژوهشکده رانشگرهای فضایی، پژوهشگاه فضایی ایران، تبریز، ایران

3 سرپرست گروه عملگرها، پژوهشکده رانشگرهای فضایی، پژوهشگاه فضایی ایران، تبریز، ایران

10.22034.jtae.2024.8.3.3

چکیده

در این مقاله، کنترل تحمل‌پذیر عیب غیرفعال مبتنی بر مد لغزشی اصلاح‌شده تطبیقی در حضور اغتشاشات خارجی، نامعینی سیستم و عیب عملگرها برای کنترل وضعیت در ماهواره با چهار چرخ عکس‌العملی طراحی شده است. به منظور نیل به این هدف، روش کنترل مد لغزشی نهایی سریع تطبیقی، به‌دلیل مقاومت در برابر نامعینی‌های مدل نشده و طراحی روش کنترل برای مدل غیرخطی سیستم مورد استفاده قرار گرفته است. برای بهبود عملکرد کنترل‌کننده، سطح لغزش به گونه‌ای انتخاب شده است که خطای ردیابی در زمان محدود به همسایگی کوچکی از مبدا همگرا شود (که با استفاده از قانون لیاپانوف توسعه‌یافته به اثبات رسیده) و از تکینگی قانون کنترلی جلوگیری گردد. در روش پیشنهادی، با به‌کارگیری یک بهره تطبیقی در بخش رساننده قانون کنترلی مد لغزشی اثرات نامطلوب ناشی از نامعینی‌های سیستم کاهش می‌‌یابد. این امر باعث کاهش چشمگیر خطای ردیابی و در نتیجه بهبود عملکرد سیستم حلقه بسته می‌شود. همچنین، در راستای حذف پدیده چترینگ، پارامترهای تطبیقی و سطح لغزش به عنوان ضریب بخش رساننده کنترلی اعمال می‌شود. نتایج شبیه‌سازی بیانگر ردیابی وضعیت با دقت بالا، حذف چترینگ و بهبود عملکرد سیستم حلقه بسته است.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Adaptive Modified Sliding-Mode-based Attitude Control of a Satellite Under Reaction Wheel Fault

نویسندگان [English]

  • Narges Talebi Motlagh 1
  • Sevil Mohammadzadeh Sadigh 2
  • hossein beheshti 3
  • hamid Ghouchi Eskandar 2
  • Moharram Shameli 1

1 Assistant Professor, Space Thrusters Research Institute, Iranian Space Research Center, Tabriz, Iran

2 Researcher, Space Thrusters Research Institute, Iranian Space Research Center, Tabriz, Iran

3 Head of Actuators Group, Space Thrusters Research Institute, Iranian Space Research Center, Tabriz, Iran

چکیده [English]

In this paper, passive adaptive modified sliding-mode-based fault tolerant control is designed to track the desired attitude of a satellite with four reaction wheels in the presence of external disturbances, system uncertainties, and actuator fault. In order to achieve this goal, the adaptive modified fast terminal SMC has been used, due to its robustness against the unmodeled uncertainties and the design of control method for the nonlinear model of system. To improve the performance of the controller, the sliding surface is selected in a way that the tracking error converges in a finite time to a small neighborhood of the origin, which is proved using the extended Lyapunov law, and avoids the singularity of the control law. The adverse effects caused by the uncertainties are reduced using an adaptive parameter in the reaching phase of the control law. This reduces the tracking error and as a result, the performance of the closed loop system is improved. Also, the adaptive parameter and sliding surface are applied as a coefficient of the reaching phase to eliminate the chattering phenomenon. The simulation results indicate the high precision attitude tracking, chattering-free, and the improved performance of closed-loop system.

کلیدواژه‌ها [English]

  • Fault Tolerant Control
  • Satellite Attitude Control
  • Fast Terminal Sliding Mode Control
  • Finite-time convergence
  • Reaction Wheel
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