بهینه‌سازی مقاوم کنترل وضعیت ماهواره با عملگر چرخ عکس‌العملی با لحاظ عدم‌قطعیت

نوع مقاله : مقاله پژوهشی (توسعه ای)

نویسنده

استادیار، گروه مهندسی برق، دانشگاه فنی و حرفه‌ای، تهران، ایران.

چکیده

در این مقاله کنترل وضعیت تک‌محوره ماهواره صلب با عملگر چرخ عکس­العملی با فرض عدم‌قطعیت و اغتشاش بررسی شده است. به‌منظور کنترل وضعیت ماهواره از کنترل‌کننده تناسبی- انتگرالی- مشتقی (PID) استفاده شد که ضرایب آن از فرایند بهینه‌سازی مبتنی بر الگوریتم تکاملی به‌دست آمده است. برای افزایش قوام سیستم کنترل در مواجهه با عدم‌قطعیت و اغتشاش، از روش بهینه‌سازی مقاوم استفاده شده است. در روش بهینه‌سازی مقاوم ویژگی­های آماری معیار عملکرد به‌عنوان تابع هدف ترکیبی الگوریتم بهینه‌ساز لحاظ شده است. به‌منظور مقایسه منصفانه، نتایج بهینه­سازی معین و بهینه­سازی مقاوم به‌ازای عدم‌قطعیت‌های مختلف با یکدیگر مقایسه شده‌اند. چرخ عکس­العملی با دینامیک مرتبه اول و لحاظ کردن محدودیت عملی بیشینه گشتاور تولیدی مدل‌سازی شده است. عدم‌قطعیت روی مدل عملگر، لختی دورانی ماهواره و اغتشاشات خارجی با مدل تابع چگالی طیفی، اعمال گردیده و با روش بهینه LHS نمونه­برداری تصادفی شده است. نتایج حل عددی، نشانگر عملکرد مقاوم‌تر کنترل‌کننده تنظیم‌شده با روش بهینه‌سازی مقاوم در مواجهه با عدم‌قطعیت­هاست؛ به‌طوری که نمودار میانگین و معیار عملکرد تابع هدف ترکیبی نشان‌دهنده تغییرات کم‌معیار عملکرد در مواجهه با عدم‌قطعیت‌هاست البته کنترل‌کننده طراحی‌شده با روش بهینه‌سازی معین، با فرض معین بودن همه مقادیر، عملکرد مناسب‌تری دارد.

کلیدواژه‌ها

موضوعات


عنوان مقاله [English]

Robust Optimization of Satellite Attitude Control with Reaction Wheel Actuator in the Presence of Uncertainties

نویسنده [English]

  • Vahid Bohlouri
Assistant Professor, Department of Electrical Engineering, Technical and Vocational University (TVU), Tehran, Iran.
چکیده [English]

In this paper, a single - axis satellite attitude control with reaction wheel actuator was analyzed in the presence of uncertainty and external disturbance. A proportional - integral - derivative (PID) controller was used to control when the control gains were achieved with evolutionary optimization algorithm. To increase robustness, robust optimization method was used in the presence of uncertainties and disturbances. In the robust optimization method, the statistical properties of the performance criterion, expected value and standard deviation were considered as the combined objective function of the optimization algorithm. For fair comparison, deterministic and robust optimization results were compared together versus uncertainties. Reaction wheel actuator was modeled with first - order equation and practical constraint in maximum and minimum generation momentum. Uncertainty was considered on moment of inertia, external disturbance, and reaction wheel with power spectral density function sampled with LHS algorithm. The graph of the mean value and performance criteria of the combined objective function shows small changes in the objective function in the face of uncertainties. Achieved numerical solution results indicated that the tuned controller with robust optimization performed better in the presence of uncertainties although tuned controller with deterministic optimization performed better assuming certain values. 

کلیدواژه‌ها [English]

  • Satellite attitude control
  • Robust optimization
  • Reaction wheel
  • Uncertainty
[1] Ley, W., Wittmann, K., & Hallmann, W. (2009). Handbook of space technology. John Wiley & Sons. https://onlinelibrary.wiley.com/doi/book/10.1002/9780470742433
[2] Sidi, M. J. (1997). Spacecraft dynamics and control: a practical engineering approach. Cambridge university press. https://www.cambridge.org/core/books/spacecraft-dynamics-and-control/E9CAEE81CD09527C99497FA8C7C35B0A
[3] Bryson, A. E. (1993). Control of spacecraft and aircraft. Princeton university press Princeton, New Jersey. https://doi.org/10.1515/9781400880034
[4] Wertz, J. R. (2012). Spacecraft attitude determination and control. Springer Science & Business Media. https://link.springer.com/book/10.1007/978-94-009-9907-7
[5] Fuchs, M., Neumaier, A., & Girimonte, D. (2007). Uncertainty modeling in autonomous robust spacecraft system design. In Proceedings in Applied Mathematics and Mechanics (pp. 41-42). https://onlinelibrary.wiley.com/doi/abs/10.1002/pamm.200700450
[6] Chen, S.-M., & Dong, Y.-F. (2011). Satellite Attitude Tracking Controller Optimization Based on Particle Swarm Optimization. Procedia Engineering, 15, 526-530. https://doi.org/10.1016/j.proeng.2011.08.100
[7] Cooper, M. A., & Smeresky, B. (2020). An Overview of Evolutionary Algorithms toward Spacecraft Attitude Control. In Advances in Spacecraft Attitude Control (pp. 51-72). https://doi.org/10.5772/intechopen.89637
[8] Li, J., Zhang, S., Liu, X., & He, R. (2017). Multi-objective evolutionary optimization for geostationary orbit satellite mission planning. Journal of Systems Engineering and Electronics, 28(5), 934-945. https://doi.org/10.21629/JSEE.2017.05.11
[9] Beyer, H.-G., & Sendhoff, B. (2007). Robust optimization – A comprehensive survey. Computer Methods in Applied Mechanics and Engineering, 196(33), 3190-3218 .
https://doi.org/10.1016/j.cma.2007.03.003
[10] Rao, S. S. (2019). Engineering optimization: theory and practice. John Wiley & Sons. https://doi.org/10.1002/9781119454816
[11] Farquhar, R. W., Aeronautics, S., & Astronautics, S. (1966). Analog Studies of the Limit-Cycle Fuel Consumption of a Spinning Symmetric Drag-Free Satellite. Stanford University, Department of Aeronautics and Astronautics. https://ntrs.nasa.gov/citations/19670001569
[12] Moghadaszadeh Bazaz, S., Bohlouri, V., & Jalali Naini, S. H .(2016) .Attitude Control Of A Rigid Satellite With Pulse-Width Pulse-Frequency Modulation Using Observer-Based Modified Pid Controller. Modares Mechanical Engineering, 16(8), 139-148 .
[13] Xiaoping, S., & Guoping, Y. (2013, May 25-27). Robust attitude tracking control scheme for flexible spacecraft with vibration suspension. 2013 25th Chinese Control and Decision Conference (CCDC), Guiyang, China. https://ieeexplore.ieee .org/abstract/document/6561260
[14] Duan, C., Zhang, S., Zhao, Y., & Kong, X. (2014) .Robust Control Allocation among Overactuated Spacecraft Thrusters under Ellipsoidal Uncertainty. Abstract and Applied Analysis, 2014, 950127. https://doi.org/10.1155/2014/950127
[15] Hu, Q., Li, B., & Zhang, Y. (2013). Robust attitude control design for spacecraft under assigned velocity and control constraints. ISA Transactions, 52(4), 480-493. https://doi.org/10.1016/j.isatra.2013.03.003
[16] Pirouzmand, F., Ghahramani, N., & Arvan, M. R. (2014). Robust Predictive Controller design using LMI for Satellite Attitude Control System. Tabriz Journal Of Electrical Engineering, 44(4), 9-21 .
[17] Shahravi, M., Kabganian, M., & Alasty, A. (2006). Adaptive robust attitude control of a flexible spacecraft. International Journal of Robust and Nonlinear Control: IFAC‐Affiliated Journal, 16(6), 287-302. https://doi.org/10.1002/rnc.1051
[18] Bohlouri, V., Ebrahimi, M., & Jalali-Naini, S. (2018, May 2-7). Robust Optimization of Satellite Attitude Control with Thruster in Presence of Disturbances. 25 th Annual International Mechanical Engineering Conference, Tehran, Iran .
[19] Bohlouri, V., Ebrahimi, M., & Naini, S. H. J. (2017, May 19-21). Robust optimization of satellite attitude control system with on-off thruster under uncertainty. 2017 International Conference on Mechanical, System and Control Engineering (ICMSC), St. Petersburg, Russia https://ieeexplore.ieee.org/abstract/document/7959495
[20] Bohlouri, V., & Jalali-Naini, S. (2018). Robust optimization of satellite attitude control with thruster actuators based on combined objective function. Journal of Space Science and Technology, 10(4), 55-66 .
[21] Bialke, B. (1998). High fidelity mathematical modeling of reaction wheel performance. 21st Annual American Astronautical Society Guidance and Control Conference, https://ci.nii.ac.jp/naid/10010248518 /
[22] Bohlouri, V., Kaviri, S., Taghinezhad, M., Naddafi Pour Meibody, M., & Seyedzamani, S. (2018). Modeling and System Identification of a reaction wheel with experimental data. Modares Mechanical Engineering, 17(11), 437-446 .
[23] Sohrabzadeh, K., Mehdiabadi Mehran., Asadi Meysam,. (2009). Determination of optimal model of reactive wheel of satellite situation control system with the aim of detecting failure. 8th iranian aerospace association conference ,Isfahan, Iran. https://civilica.com/doc/75990 /
[24] Bellar, A., & Mohammed, M. A. S. (2019). Satellite inertia parameters estimation based on extended Kalman Filter. Journal of Aerospace Technology and Management, 11. https://doi.org/10.5028/jatm.v11.1016
[25] Venanzi, I., Materazzi, A., & Ierimonti, L. (2015). Robust and reliable optimization of wind-excited cable-stayed masts. Journal of Wind Engineering and Industrial Aerodynamics, 147, 368-379. https://doi.org/10.1016/j.jweia.2015.07.011