Journal of Space Science and Technology

Journal of Space Science and Technology

A Fixed-time Stable Output Feedback Non-singular Fast Terminal Sliding Mode Design for Attitude Control of a Rigid Spacecraft Considering External Disturbances and System Uncertainties

Document Type : Original Research Paper

Authors
1 Ph.D student, Department of Satellite Technology Engineering, Faculty of New Technologies, Iran University of Science and Technology, Tehran, Iran
2 Assistant Professor, Department of Satellite Technology Engineering, Faculty of New Technologies, Iran University of Science and Technology, Tehran, Iran
3 PhD student,, Department of Satellite Technology Engineering, Faculty of New Technologies, Iran University of Science and Technology, Tehran, Iran
Abstract
This study introduces a novel spacecraft attitude control framework designed to operate reliably under uncertainties and external disturbances. At its core lies a dual-component strategy: a controller and a disturbance observer, both engineered for fixed-time convergence. Unlike conventional finite-time methods, where stabilization speed depends on initial conditions, this approach guarantees a preset stabilization window, tunable via controller parameters giving engineers precise command over performance timelines. By modeling spacecraft attitude dynamics using modified Rodriguez parameters (MRP), the system is cast into a second-order nonlinear structure. A non-singular terminal sliding surface is developed to enforce fixed-time convergence, enabling the derivation of robust control inputs. To address real-world unpredictability, a universally robust exact differentiator (URED) observer estimates and neutralizes disturbances within the same fixed timeframe, ensuring seamless compensation. Stability is validated using Lyapunov theory, while comparative simulations against existing methods demonstrate that the proposed framework achieves faster convergence and superior tracking accuracy for both controller and observer. These advancements set it as a promising solution for critical space missions requiring rapid, precise attitude control, such as satellite docking or deep-space exploration.
Keywords
Subjects

Article Title Persian

طراحی کنترل‌کننده مد لغزشی ترمینالی غیر‌تکین سریع فیدبک خروجی با پایداری زمان ثابت به‌منظور کنترل وضعیت یک فضاپیمای صلب با درنظر گرفتن اثر اغتشاشات خارجی و عدم قطعیت‌های سیستمی

Authors Persian

حامد سلیمانی 1
مجید بختیاری 2
جلیل بیرامزاد 3
1 دانشجوی دکتری، گروه مهندسی فناوری ماهواره، دانشکده فناوری‌های نوین، دانشگاه علم و صنعت ایران، تهران، ایران
2 استادیار، گروه مهندسی فناوری ماهواره، دانشکده فناوری‌های نوین، دانشگاه علم و صنعت ایران، تهران ، ایران
3 دانشجوی دکتری، گروه مهندسی فناوری ماهواره، دانشکده فناوری‌های نوین، دانشگاه علم و صنعت ایران، تهران، ایران
Abstract Persian

این پژوهش یک چارچوب نوین برای کنترل وضعیت فضاپیما معرفی می‌کند که با هدف عملکرد پایدار در شرایط عدم قطعیت و اغتشاشات خارجی طراحی شده است. هسته اصلی این سیستم مبتنی بر یک راهبرد دوجزئی شامل یک کنترل‌کننده و یک رویتگر اغتشاشات است که هر دو با الگوریتم‌های همگرایی در زمان ثابت طراحی شده‌اند. برخلاف روش‌های متداول همگرایی در زمان محدود، که سرعت تثبیت به شرایط اولیه وابسته است، این چارچوب تضمین می‌کند سیستم در یک بازه زمانی ازپیش‌تنظیم‌شده تثبیت می‌شود. این بازه با تنظیم پارامترهای کنترل‌کننده، امکان مدیریت دقیق زمانبندی عملکرد را فراهم می‌سازد. دینامیک وضعیت فضاپیما با استفاده از پارامترهای رودریگز اصلاح‌شده به عنوان یک ساختار غیرخطی مرتبه دوم مدل‌سازی شده است. برای تحقق همگرایی در زمان ثابت و استخراج ورودی‌های کنترلی مقاوم، یک سطح لغزش ترمینال غیرتکین توسعه یافته است که از مشکلات تکینی در روش‌های مرسوم اجتناب می‌کند. برای مقابله با عدم قطعیت‌های دنیای واقعی، یک رویتگر مشتق‌گیر دقیق و مقاوم جهانی طراحی شده که اغتشاشات را در همان بازه زمانی ثابت تخمین زده و خنثی می‌کند و جبران‌سازی بی‌وقفه را ممکن می‌سازد. پایداری سیستم با استفاده از نظریه لیاپانوف به‌صورت تحلیلی تأیید شده است. شبیه‌سازی‌های مقایسه‌ای با روش‌های موجود نشان می‌دهد چارچوب پیشنهادی به همگرایی سریعتر و دقت ردیابی بالاتر در هر دو بخش کنترل‌کننده و رویتگر دست می‌یابد. این پیشرفت‌ها، این سیستم را به عنوان راهکاری امیدوارکننده برای مأموریت‌های حیاتی فضایی نظیر اتصال ماهواره‌ها، کنترل وضعیت در مدارهای پیچیده، و اکتشافات اعماق فضا مطرح می‌کند که نیازمند واکنش‌های سریع، دقت فوق‌العاده و مطمئن هستند.

Keywords Persian

ماهواره
کنترل وضعیت
رویتگر مشتق‌گیر دقیق و مقاوم جهانی
پایداری زمان ثابت
مد لغزشی ترمینال غیرتکین
[1] S. Shikai, Z. Qun, T. Bailing, and W. Fang, "Finite-time sliding mode attitude control for rigid spacecraft without angular velocity measurement," Journal of the Franklin Institute, vol. 354, no. 12, pp. 4656-4674, 2017, https://doi.org/10.1016/j.jfranklin.2017.04.020.
[2] J. Beyramzad, K. Daneshjou, and E. Khanmirza, "Design a finite-time chattering free attitude controller for rigid spacecrafts without angular velocity measurement using interval type-II fuzzy logic nonsingular terminal sliding mode and nonlinear extended state observer,” in 21st International Conference of Iranian Aerospace Society, Tehran, Iran, 2023, pp. 1-8.
[3] Y. Shtessel, C. Edwards, L. Fridman, and A. Levant, Sliding Mode Control and Observation, New York: Birkhäuser, 2014, https://doi.org/10.1007/978-0-8176-4893-0.
[4] J. Liu and X. Wang, Advanced Sliding Mode Control for Mechanical Systems, Berlin: Springer, 2012, https://doi.org/10.1007/978-3-642-20907-9.
[5] X. Yu, Y. Feng, and Z. Man, "Terminal sliding mode control–An overview," IEEE Open Journal of the Industrial Electronics Society, vol. 2, pp. 36-52, 2020, https://doi.org/10.1109/OJIES.2020.3040412.
[6] 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, https://doi.org/10.1016/j.isatra.2013.08.008.
[7] H. Yadegari, J. Beyramzad, and E. Khanmirza. "Magnetorquers-based satellite attitude control using interval type-II fuzzy terminal sliding mode control with time delay estimation," Advances in Space Research, vol. 69, no. 8, pp. 3204-3225, 2022, https://doi.org/10.1016/j.asr.2022.01.018.
[8] S. Dey, D. K. Giri, K. Gaurav, and V. Laxmi, "Robust nonsingular terminal sliding mode attitude control of satellites," Journal of Aerospace Engineering, vol. 34, no. 1, 2021, 10.1061/(ASCE)AS.1943-5525.0001224.
[9] P. M. Tiwari, S. Janardhanan, and M. Nabi, "Rigid spacecraft attitude control using adaptive non-singular fast terminal sliding mode," Journal of Control, Automation and Electrical Systems, vol. 26, pp. 115-124, 2015, https://doi.org/10.1007/s40313-014-0164-0.
[10] Y. Guo, B. Huang, S. M. Song, A. J. Li, and C. Q. Wang, "Robust saturated finite-time attitude control for spacecraft using integral sliding mode," Journal of Guidance, Control, and Dynamics, vol. 42, no. 2, pp. 440-446, 2019, https://doi.org/10.2514/1.G003520.
[11] A. Sahamijoo, F. Piltan, M. H. Mazloom, M. R. Avazpour, H. Ghiasi, and N. B. Sulaiman, "Methodologies of chattering attenuation in sliding mode controller," International Journal of Hybrid Information Technology, vol. 9, no. 2, pp. 11-36, 2016, https://doi.org/10.14257/ijhit.2016.9.2.02.
[12] F.Shokouhi and A. H.  Davaie Markazi, "A new continuous approximation of sign function for sliding mode control," in 6th International Conference on Robotics and Mechatronics (ICRoM), Tehran, Iran, 2018.
[13] V. Utkin, A. Poznyak, Y. Orlov, and A. Polyakov, "Conventional and high order sliding mode control," Journal of the Franklin Institute, vol. 357, no. 15, pp. 10244-10261, 2020, https://doi.org/10.1016/j.jfranklin.2020.06.018.
[14] L. Fridman, J. A. Moreno, B. Bandyopadhyay, S. Kamal, and A. Chalanga, "Continuous nested algorithms: The fifth generation of sliding mode controllers," in Recent Advances in Sliding Modes: from Control to Intelligent Mechatronics, X. Yu and M. Önder Efe, Eds. Springer Cham, 2015, pp. 5-35, https://doi.org/10.1007/978-3-319-18290-2_2.
[15] P. M. Tiwari, S. Janardhanan, and M. un Nabi, "Attitude control using higher order sliding mode," Aerospace Science and Technology, vol. 54, pp. 10-113, 2016, https://doi.org/10.1016/j.ast.2016.04.012.
[16] Y. Guo, b. Huang, J. H. Guo, A. Li, and C.Q. Wang, "Velocity-free sliding mode control for spacecraft with input saturation," Acta Astronautica, vol. 154, pp. 1-8, 2019, https://doi.org/10.1016/j.actaastro.2018.10.045.
[17] K. Zhang, G. R. Duan, and M. D. Ma, "Dynamic output feedback sliding mode control for spacecraft hovering without velocity measurements," Journal of the Franklin Institute, vol. 356, no. 4, pp. 1991-2014, 2019, https://doi.org/10.1016/j.jfranklin.2019.01.030.
[18] L. Yuan, G. Ma, C. Li, and B. Jiang, "Finite-time attitude tracking control for spacecraft without angular velocity measurements," Journal of Systems Engineering and Electronics, vol. 28, no. 6, pp. 1174-1185, 2017, https://doi.org/10.21629/JSEE.2017.06.15.
[19] Q. Hu and B. Jiang, "Continuous finite-time attitude control for rigid spacecraft based on angular velocity observer," IEEE Transactions on Aerospace and Electronic Systems, vol. 54, no. 3, pp. 1082-1092, 2017, https://doi.org/10.1109/TAES.2017.2773340.
[20] M. Malekzadeh and H. Sadeghian, "Attitude control of spacecraft simulator without angular velocity measurement," Control Engineering Practice, vol. 84, pp. 72-81, 2019, https://doi.org/10.1016/j.conengprac.2018.11.011.
[21] A. Bani Younes and D. Mortari, "Derivation of all attitude error governing equations for attitude filtering and control," Sensors, vol. 19, no. 21, 2019, Art. no. 4682, https://doi.org/10.3390/s19214682.
[22] A. Bani Younes, D. Mortari, J. D. Turner, and J. L. Junkins, "Attitude error kinematics," Journal of Guidance, Control, and Dynamics, vol. 37, no. 1, pp. 330-336, 2014, https://doi.org/10.2514/1.60928.
[23] N. Nazari, H. Moladavoudi, and J. Beyramzad, "Finite time sliding mode control for agile rigid satellite with CMG actuators using fast high-order sliding mode observer," Aerospace Systems, vol. 7, pp. 363-383, 2024, https://doi.org/10.1007/s42401-024-00283-4.
[24] J. L. Crassidis and F. Landis Markley, "Attitude estimation using modified rodrigues parameters," in Flight Mechanics/Estimation Theory Symposium, Greenbelt, Maryland, 1996, pp. 71-86.
[25] Z. Zuo, "Non‐singular fixed‐time terminal sliding mode control of non‐linear systems," IET control theory & applications, vol. 9, no. 4, pp. 545-552, 2015, https://doi.org/10.1049/iet-cta.2014.0202.
[26] E. Cruz-Zavala, J. A. Moreno, and L. M. Fridman, "Uniform robust exact differentiator," IEEE Transactions on Automatic Control, vol. 56, no. 11, pp. 2727-2733, 2011, https://doi.org/10.1109/TAC.2011.2160030.
[27] T. N. Truong, A. T. Vo, H. J. Kang, and T. D. Le, "An observer-based fixed time sliding mode controller for a class of second-order nonlinear systems and its application to robot manipulators," in 18th International Conference, ICIC, Conference proceedings, Xi'an, China, 2022, https://doi.org/10.1007/978-3-031-13832-4_44.
[28] V. I. Utkin, Sliding Modes in Control and Optimization, Berlin, Germany: Springer, 2013, https://doi.org/10.1007/978-3-642-84379-2_6.
[29] X. T. Tran and H. J. Kang, "Continuous adaptive finite-time modified function projective lag synchronization of uncertain hyperchaotic systems," Transactions of the Institute of Measurement and Control, vol. 40, no. 3, pp. 853-860, 2018, https://doi.org/10.1177/014233121667045.
[30] M. Azadmanesh, J. Roshanian, and M. Hassanalian, "Fast terminal sliding mode control for the soft landing of a space robot on an asteroid considering a barycentric gravitational model," Journal of Aerospace Science and Technology, vol. 16, no. 1, pp. 66-76, 2023, https://doi.org/10.22034/jast.2023.394618.1147.
[31] M. Azadmanesh, J. Roshanian, and M. Hassanalian, "A fuzzy fast terminal approach for tracking a probe around an asteroid," Journal of Aerospace Science and Technology, vol. 16, no. 2, pp. 1-10, 2023
Volume 18, Issue 2
2025
Pages 70-82

  • Receive Date 23 March 2025
  • Revise Date 07 May 2025
  • Accept Date 01 June 2025
  • First Publish Date 22 June 2025