Introducing the Nonlinear State Control Algorithm of the Air Bearing Laboratory Simulator Based on the Gain Coefficients Dependent on the State Variables

Ahangarani Farahani, Alireza; Adami, Amirhossain; Arefkhani, Hamed

doi:10.30699/jsst.2023.1437

Introducing the Nonlinear State Control Algorithm of the Air Bearing Laboratory Simulator Based on the Gain Coefficients Dependent on the State Variables

Document Type : Original Research Paper

Authors

Alireza Ahangarani Farahani ¹

Amirhossain Adami ¹

Hamed Arefkhani ²

¹ Assistant Professor, Aerospace University Complex, Malek Ashtar University of Technology, Tehran, Iran

² Ph.D., Aerospace University Complex, Malek Ashtar University of Technology, Tehran, Iran

10.30699/jsst.2023.1437

Abstract

In this article, a new approach has been presented in the design of a satellite's status controller using reaction wheels. First, a non-linear controller whose gains depend on the state variables at any moment is proposed. In the first step, the process of extracting control coefficients using the GA optimizer is described. Then, using the results of a number of tests, sufficient data for meta-modeling of the system is extracted and the relevant control gain functions are optimized using the data bank. The input of the mentioned function is the system states and its output is the control coefficients. Finally, a simulator platform was used to determine and control the position of the satellite based on the air bearing to evaluate the proposed approach. Laboratory test results show that the performance of the proposed method is up to 30% better than the classical PID controller with fixed coefficients.

Keywords

Reaction wheels

Attitude control

Attitude determination and control simulator platform

Air bearing

Subjects

Space subsystems design: (navigation, control, structure and…)

Article Title Persian

ارایه الگوریتم کنترل غیرخطی‌ وضعیت شبیه‌ساز آزمایشگاهی یاتاقان هوایی مبتنی‌بر ضرایب بهره وابسته به متغیرهای حالت

Authors Persian

علیرضا آهنگرانی فراهانی ¹

امیرحسین آدمی ¹

حامد عارف خانی ²

¹ استادیار، مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر، تهران، ایران

² دکتری، مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر، تهران، ایران

Abstract Persian

در این مقاله به ارائه یک رویکرد جدید در طراحی کنترل‌کننده وضعیت یک ماهواره با استفاده از چرخ‌های عکس‌العملی پرداخته شده ‌است. ابتدا یک کنترل‌کننده غیرخطی که بهره‌های آن در هر لحظه وابسته به متغیرهای حالت است پیشنهاد می‌گردد. در گام اول، روند استخراج ضرایب کنترل با استفاده از بهینه‌ساز GA تشریح می‌گردد. سپس با استفاده از نتایج تعدادی آزمایش، داده کافی برای شبه مدل‌سازی (Meta Modelling) سیستم استخراج شده و با استفاده از بانک داده‌ها، تابع بهره‌های کنترلی مربوطه بهینه‌سازی می‌گردند. ورودی تابع مذکور حالت‌های سیستم و خروجی آن ضرایب کنترلی است. در نهایت از یک پلتفرم شبیه‌ساز تعیین و کنترل وضعیت ماهواره مبتنی بر یاتاقان هوایی جهت ارزیابی رویکرد پیشنهادی استفاده گردید. نتایج تست آزمایشگاهی نشان می‌دهد عملکرد روش پیشنهاد شده تا 30% بهتر از کنترل کننده کلاسیک PID با ضرایب ثابت است.

Keywords Persian

چرخ‌های عکس‌العملی

کنترل وضعیت

پلتفرم شبیه‌ساز تعیین و کنترل وضعیت

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