نویسندگان

چکیده

اخیرًا عملگرهای جدیدی به نام کنترلرهای مومنتوم سیالی برای کنترل وضعیت ماهواره پیشنهاد شده است. این عملگرها نسبت به دیگر عملگرهای ذخیره‌ساز مومنتوم مثل چرخ‌های عکس‌العملی و CMG‌ها، دارای نسبت گشتاور اعمالی به وزن بالاتری، جانمایی و مونتاژ راحت‌تر، ارتعاش انتقالی کمتر و... هستند. اما یکی از مشکلات پیاده‌سازی چنین سیستم‌هایی در عمل، پیچیدگی در مدل‌سازی ریاضی این عملگرها می‌باشد. این امر باعث شده است که اکثر محققان از یک مدل ساده شده، برای طراحی سیستم کنترلی استفاده کنند، بدون آنکه عدم قطعیت‌ها در مدل ساده شده را در نظر بگیرند. در این مقاله برای رفع این مشکل از یک روش کنترلی مود لغزشی- تطبیقی استفاده شده که در برابر این نبود قطعیت‌ها در مدل مقاوم است و همچنین می‌تواند حد بالای این عدم قطعیت‌ها را تخمین بزند، بدون آنکه نیاز باشد تا از عملگرهای بزرگ‌تر برای اطمینان از پایداری سیستم استفاده کرد. با توجه به نتایج شبیه‌سازی، می‌توان مشاهده کرد که سیستم کنترلی مورد طراحی قادر است که ماهواره را در کمترین زمان ممکن و بدون فراجهش به وضعیت مطلوب برساند.

کلیدواژه‌ها

عنوان مقاله [English]

Attitude Control System Design Based on Fluidic Momentum Controllers under Adaptive Sliding Mode

نویسندگان [English]

  • A.H. Taghavi
  • A. Soleymani
  • T. Shojaee

چکیده [English]

Recently, new actuators known as fluidic momentum controllers (FMC) have been proposed for satellite attitude control. This actuator has many advantages such as high applied torque to weight ratio, easiness in assembly, low transmitted vibration and so on respect to the other momentum exchange devices like momentum/reaction wheels or CMGs. However, one of the main problems in implementing such actuators is complexity in mathematic modeling of them. This issue makes many researchers to use a simplified model for control system designing without to consider uncertainty in this simplified model. In this paper for eliminating of this problem, an adaptive sliding mode control (SMC) has been used in this article. This control method is not also robust respect to uncertainties but also can estimate over threshold of them without necessity to use larger and heavier actuators to be sure of satellite stability. According to the results, we can observe that proposed control system is capable to reach satellite to the desire attitude in minimum time and without overshoot.

کلیدواژه‌ها [English]

  • Satellite attitude control
  • Fluidic Momentum Controller (FMC)
  • Adaptive sliding mode control
  • Uncertainly
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