نوع مقاله : مقالة تحقیقی (پژوهشی)
نویسندگان
1 استادیار، مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر، تهران، ایران
2 دکتری، مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر، تهران، ایران
چکیده
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.
کلیدواژه‌ها
موضوعات
عنوان مقاله [English]
Introducing the Nonlinear State Control Algorithm of the Air Bearing Laboratory Simulator Based on the Gain Coefficients Dependent on the State Variables
نویسندگان [English]
- 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
چکیده [English]
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.
کلیدواژه‌ها [English]
- Reaction wheels
- Attitude control
- Attitude determination and control simulator platform
- Air bearing
- J. He ,and et al. "Satellite Control and Data Processing Unit Software Design Based on Multi-Core Processor" in 2020 Internatinal Conference on Sensing, Measurment & Data Analytics in era of Artificial Intelligence, pp. 352-356, IEEE, 2020.
- W. Yang, J.Wang, S.Li , and L.Wang , "Attitude Fault Tolerant Control for Satellite Under Actuator Fault and Inertial Sensor Fault, " , In 39the Chinese Control Conference,(CCC), pp. 3439-3443, IEEE, 2020.
- A. Rahimi , K.D. Kumar and H.Alighanbari , "Fault Isolation of Reaction Wheels for Satellite Attitude Control, " IEEE Transactions On Aerospace And Electronic Systems Vol. 56, No. 1, pp. 610-629, 2020.
- T.H Kwan , and et al, " An air Bbearing table for satellite attitude control simulation", in 2015 IEEE 10th Conference on Industrial Electronics and Applications (ICIEA), pp. 1420-1425, IEEE, 2015.
- R.F. Costa1, O. Saotome, E. Rafkova, " Simulation and validation of satellite attitude control algorithms in a spherical air bearing", Journal of Control, Automation and Electrical Systems, vol. 30, pp. 716–727, 2019.
- I. Ofodile, A. Slavinskis, H.Ehrpais, and G.K. Anbarjafari , "Stabilised LQR Control and Optimised Spin Rtate Control for Nanosatellites, " in 2019 9th International Conference on Recent Advances in Space Technologies,(RAST) pp. 715-722, IEEE, 2019.
- H. Taei, M. and et al. "Optimal Control of a Tri-Axial Spacecraft Simulator Test Bed Actuated by Reaction Wheels", Journal of Space Science and Technology, Vol. 8, No. 25, pp. 35-45, 2016 (in Persian).
- A. Aydogan, O. Hasturk, "Adaptive LQR stabilization control of reaction wheel for satellite systems", in 14th International Conference on Control, Automation, Robotics & Vision,(ICARC), pp. 1-6, Phuket, Thailand, IEEE, 2016.
- A.R. Kosari, M. Peyrovani, M. Fakoor. and H.Nejat, "Design of LQG/LTR Controller for Attitude Control of Geostationary Satellite Using Reaction Wheels, " Modarres Mechanical Engineering, Vol. 13, No. 14, pp. 210-219, 2014.(in Persian).
- M. Navabi. and R. Hosseini, "Spacecraft Quaternion Based Attitude Input-Output Feedback Linearization Control Using Reaction Wheels", in 8th International Conference on Recent Advances In Space Technologies (RAST), pp. 97-103, Turkey, IEEE, 2016.
- M. Malekzadeh, M. Sabouhi, ang M. Rezayati , " Designing Nonlinear Robust Controller for Spacecraft Attitude Control Subsystem Simulator", Journal of Mechanical Engineering, vol. 48, no. 2, pp. 329-338, 2019 (in Persian).
- Z. Song, H. Li. and K. Sun, " Finite-Time Control for Nonlinear Spacecraft Attitude Based on Terminal Sliding Mode Technique", ISA Transactions, Vol. 53, No. 1, pp.117–124, 2014.
- L. Zhao, and Y. Jia , " Finite-Time Attitude Tracking Control for a Rigid Spacecraft Using Time-Varying Terminal Sliding Mode Techniques" International Journal of Control, Vol. 88, No.6, pp. 1150-1162, 2014.
- P.M. Tiwari, S. Janardhanan . and M.Nabi, "Rigid Spacecraft Attitude Control Using Adaptive Integral Second Order Sliding Mode", Aerospace Science and Technology, Vol. 48, pp. 50-57, 2015, DOI10.1016/j.ast.2014.11.017
- C. Pukdeboon, and A.S. Zinober, "Control Lyapunov Function Optimal Sliding Mode Controllers for Attitude Tracking of Spacecraft", Journal of the Franklin Institute, Vol. 349, No. 2, pp. 456-475, 2012.
- M. Navabi. and N. Safari Hashkavaei, "Nonlinear Attitude Control of Satellite Using Optimal Adaptive and Fuzzy Control Methods, " in 2020 8th Iranian Joint Congress on Fuzzy Control Intelligent Systems,(CFIS) pp 51-55, IEEE, 2020.
- A.H. Tavakoli, A. Kalhor, and S.M.M Dehghan, "Implementation of Three Axis Attitude Controllers for Evaluation of a Micro-gravity Satellite Simulator, "Space Science and Technology (JSST), Vol 5, No. 2, pp. 59-68, 2012 (in Persian)
- P. Razzaghi, E. AlKhatib, K.S Alluhydan , and Y. Hurmuzlu. "H2-H∞ Model Reference Adaptive Control of Tethered Satellite System, " in 2020 IEEE Aerospace Conference, pp. 1-8, 2020.
- H. Arefkhani, S.H. Sadati and M. Shahravi, " Satellite Attitude Control Using a Novel Constrained Magnetic Linear Quadratic Regulator", Journal of Control Engineering Practice, Vol. 101, pp. 1-11, 2020.
- Y. Liu, J. Zhou, H. Chen and x. Mu, "Experimental Research for Flexible Satellite Dynamic Simulation on Three-Axis Air-Bearing Table", Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering. Vol. 227, No. 2, pp. 369-380, 2013.
- H. Arefkhani, M. Mehdi-Abadi, and S. M. M. Dehghan, "Satellite Spin Stabilization by Magnetic Torquers and Validation with Air-Bearing Simulator," Journal of Space Science and Technology, vol. 9, no. 2, pp. 25-34, 2016 (in Persian)
)