Journal of Space Science and Technology

Journal of Space Science and Technology

Adaptive Robust Attitude Control and Vibration Suppression of a Flexible Satellite in Imaging Maneuver

Document Type : Original Research Paper

Authors
Faculty of Aerospace Engineering, K. N. Toosi University of Technology, Tehran, Iran
Abstract
Deployable solar arrays serve as the primary power source for many remote-sensing satellites. These arrays, characterized by their long, wide, and thin structure, exhibit significant flexibility, posing challenges to satellite attitude control. Remote sensing missions require rapid maneuvers to capture images within strict time constraints, yet such maneuvers induce oscillations in the deployable solar arrays, degrading image quality. This study presents an advanced attitude control strategy to mitigate the uncertainties introduced by solar array vibrations. An adaptive robust attitude controller is implemented to address model uncertainties and environmental disturbances. While the adaptive robust control method effectively manages attitude maneuvers with slew rates below 1 deg/s, high-frequency vibration amplitudes increase during rapid attitude adjustments. A dual-control approach is introduced to counteract this effect, integrating an adaptive robust attitude controller with an input shaping technique for vibration suppression. Simulation results confirm that the proposed control strategy enhances pointing accuracy, stability, and vibration attenuation, improving imaging performance in dynamic operational scenarios.
Keywords
Subjects

Article Title Persian

کنترل وضعیت مقاوم تطبیقی و کاهش ارتعاشات یک ماهواره انعطاف پذیر در مانور تصویربرداری

Authors Persian

محمد ضرورتی
مهران میرشمس
مرتضی طایفی
دکتری، دانشکده مهندسی هوافضا، دانشگاه صنعتی خواجه نصیرالدین طوسی، تهران، ایران
Abstract Persian

در ماهواره‌های سنجش از راه دور، به‌منظور تأمین انرژی الکتریکی از آرایه های خورشیدی بازشونده استفاده می شود. آرایه های خورشیدی دارای طول و عرض زیاد و ضخامت کم می‌باشند. لذا آرایه‌های خورشیدی انعطاف‌پذیر هستند. انعطاف‌پذیری آرایه‌های خورشیدی دشواری هایی را برای کنترل وضعیت ماهواره به وجود می‌آورد. از طرف دیگر، برای ماهواره‌هایی با مأموریت سنجش از راه دور، الزاماتی نظیر تصویربرداری با حجم زیاد، قابلیت مانور به منظور تصویربرداری از اهداف موردنظر و محدودیت زمانی مد تصویربرداری تعریف می شود. به‌منظور برآورده نمودن این ملزومات، نیاز به مانور سریع وضعیت می‌باشد که باعث می‌شود آرایه های خورشیدی بازشونده ارتعاش نماید و کیفیت تصاویر گرفته‌شده کاهش یابد. در این مقاله کنترل‌کننده وضعیتی طراحی می گردد که بر عدم قطعیت‌هایی که در مدل به دلیل انعطاف پذیری آرایه های خورشیدی به وجود آمده است فائق آید. در این راستا، با توجه به عدم قطعیت‌هایی موجود در مدل ماهواره انعطاف‌پذیر و حضور اغتشاشات خارجی، از روش کنترل وضعیت مقاوم تطبیقی استفاده می شود. روش کنترل وضعیت مقاوم تطبیقی در مانورهایی با نرخ دوران کمتر از یک درجه بر ثانیه عملکرد خوبی دارد. اما در مانورهای سریع وضعیت، دامنه نوسانات فرکانس بالای زاویه‌ای ماهواره یا جیتر افزایش می یابد. لذا در ادامه، یک روش کنترلی مضاعف برای کاهش ارتعاشات ارائه می شود. در واقع روش کنترل پیشنهادی جهت کاهش ارتعاشات، کنترل وضعیت مقاوم تطبیقی مبتنی بر تکنیک شکل‌دهی ورودی می‌باشد. نتایج شبیه سازی نشان می دهد که روش کنترل پیشنهادی، در مانور سریع وضعیت، دقت نشانه روی و پایداری نشانه روی را بطور قابل ملاحظه ای بهبود می دهد و عملکرد خوبی در کاهش ارتعاشات دارد.

Keywords Persian

ماهواره انعطاف‌پذیر
مانور سریع
مقاوم تطبیقی
کاهش ارتعاشات
شکل دهی ورودی
[1]   L. Mazzini, Springer Aerospace Technology Flexible Spacecraft Dynamics, Control and Guidance, Springer Cham, 2016, https://doi.org/10.1007/978-3-319-25540-8 .
[2]   P. Gasbarri, R. Monti, and M. Sabatini, "Very large space structures: Non-linear control and robustness to structural uncertainties," Acta Astronautica, vol. 93, pp. 252–265, 2014, https://doi.org/10.1016/j.actaastro.2013.07.022.
[3]   A. Ebrahimi, S. A. A. Moosavian, and M. Mirshams, "Minimum-time optimal control of flexible spacecraft for rotational maneuvering," in International Conference on Control Applications, Taipei, Taiwan, 2004, pp. 961–966, https://doi.org/10.1109/CCA.2004.1387494.
[4]   M. R. Dehghan Nayeri, A. Alasty, and K. Daneshjou, "Neural optimal control of flexible spacecraft slew maneuver," Acta Astronautica, vol. 55, no. 10, pp. 817–827, 2004, https://doi.org/10.1016/j.actaastro.2004.04.002.
[5]   U. Javaid, Z. Zhen, S. Shahid, D. S. Ibrahim, and S. Ijaz, "Output feedback attitude control of flexible spacecraft under actuator misalignment and input nonlinearities," Journal of Vibration and Control, vol. 30, no. 7–8, pp. 1783–1801, 2024,
https://doi.org/10.1177/10775463231171386.
[6]   R. Q. Dong, X. Dong, A. G. Wu, and Y. Zhang, "Dynamic sliding mode attitude tracking control for flexible spacecraft," in 28th International Symposium on Industrial Electronics, Vancouver, BC, Canada, 2019, pp. 509–514, https://doi.org/10.1109/ISIE.2019.8781505.
[7]   A. Li, M. Liu, and Y. Shi, "Adaptive sliding mode attitude tracking control for flexible spacecraft systems based on the Takagi-Sugeno fuzzy modelling method," Acta Astronautica, vol. 175, pp. 570–581, 2020, https://doi.org/10.1016/j.actaastro.2020.05.041.
[8]   Z. Hou and X. Lan, "Adaptive sliding mode and RBF neural network based fault tolerant attitude control for spacecraft with unknown uncertainties and disturbances," Advances in Space Research, vol. 74, no. 4, pp. 1680–1692, 2024, https://doi.org/10.1016/j.asr.2024.05.021.
[9]   S. Wu, W. Chu, X. Ma, G. Radice, and Z. Wu, "Multi-objective integrated robust H∞ control for attitude tracking of a flexible spacecraft," Acta Astronautica, vol. 151, pp. 80–87, 2018, https://doi.org/10.1016/j.actaastro.2018.05.062.
[10] Y. Yu, X. Meng, K. Li, and F. Xiong, "Robust control of flexible spacecraft during large-angle attitude maneuver," Journals of Guidance, Control and Dynamics, vol. 37, no. 3, pp. 1027–1033, 2014, https://doi.org/10.2514/1.61421.
[11] Z. Ni, J. Liu, S. Wu, and Z. Wu, "Time-varying state-space model identification of an on-orbit rigid-flexible coupling spacecraft using an improved predictor-based recursive subspace algorithm," Acta Astronautica, vol. 163, Part. B, pp. 157–167, 2019, https://doi.org/10.1016/j.actaastro.2018.11.008.
[12] S. Shen and Q. Sun, "Characteristic model-based fast attitude maneuver for the complex flexible satellite," in AIAA SPACE 2015 Conference and Exposition, Pasadena, California, 2015, https://doi.org/10.2514/6.2015-4508.
[13] M. Zarourati, M. Mirshams, and M. Tayefi, "Attitude path design and adaptive robust tracking control of a remote sensing satellite in various imaging modes," Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, vol. 237, no. 9, pp. 2166–2184, 2023, https://doi.org/10.1177/09544100221148887.
[14] L. Wang, Y. Guo, W. Yao, and Q. Chen, "Adaptive robust attitude control for flexible spacecraft with control moment gyroscopes," in 12th World Congress on Intelligent Control and Automation (WCICA), Guilin, China, 2016, pp. 2376–2381, https://doi.org/10.1109/WCICA.2016.7578603.
[15] Q. Hu and G. Ma, "Variable structure control and active vibration suppression of flexible spacecraft during attitude maneuver," Aerospace Science and Technology, vol. 9, no. 4, pp. 307–317, 2005, https://doi.org/10.1016/j.ast.2005.02.001.
[16] L. Zhu, W. Song, and Q. Hu, "Active vibration suppression and attitude maneuvers of flexible spacecraft via fuzzy sliding control," in Chinese Control and Decision Conference, Yantai, China, 2008, pp. 3665–3669, https://doi.org/10.1109/CCDC.2008.4598014.
[17] I. M. da Fonseca, D. A. Rade, L. C. S. Goes, and T. de Paula Sales, "Attitude and vibration control of a satellite containing flexible solar arrays by using reaction wheels, and piezoelectric transducers as sensors and actuators," Acta Astronautica, vol. 139, pp. 357–366, 2017, https://doi.org/10.1016/j.actaastro.2017.07.018.
[18] E. Wang, S. Wu, Y. Liu, Z. Wu, and X. Liu, "Distributed vibration control of a large solar power satellite," Astrodynamics, vol. 3, no. 2, pp. 189–203, Jun. 2019, https://doi.org/10.1007/s42064-018-0046-5.
[19] Z. Hou, Y. Geng, and S. Huang, "Minimum Residual Vibrations for Flexible Satellites with Frequency Uncertainty," IEEE Transactions on Aerospace and Electronic Systems, vol. 54, no. 2, pp. 1029–1038, 2018, https://doi.org/10.1109/TAES.2017.2773321.
[20] X. Cao, C. Yue, and M. Liu, "Flexible satellite attitude maneuver via constrained torque distribution and active vibration suppression," Aerospace Science and Technology, vol. 67, pp. 387–397, 2017, https://doi.org/10.1016/j.ast.2017.04.014.
[21] B. Wie and C. T. Plescia, "Attitude stabilization of flexible spacecraft during stationkeeping maneuvers," Journals of Guidance, Control and Dynamics, vol. 7, no. 4, pp. 430–436, 1984, https://doi.org/10.2514/3.19874 .
[22] M. Zarourati, M. Mirshams, and M. Tayefi, "Designing an adaptive robust observer for underactuation fault diagnosis of a remote sensing satellite," International Journal of Adaptive Control and Signal Processing, vol. 37, no. 11, pp. 2812–2834, 2023, https://doi.org/10.1002/acs.3661.
[23] H. Li, M. D. Le, Z. M. Gong, and W. Lin, "Motion profile design to reduce residual vibration of high-speed positioning stages," IEEE/ASME Transactions on Mechatronics, vol. 14, no. 2, pp. 264–269, 2009, https://doi.org/10.1109/TMECH.2008.2012160.
[24] M. Tahmasebi and S. M. Esmailzadeh, "Modeling and co-simulating of a large flexible satellites with three reaction wheels in ADAMS and MATLAB," International Journal of Dynamics and Control, vol. 6, no. 1, pp. 79–88, 2018, https://doi.org/10.1007/s40435-016-0300-8.
[25] M. Zarourati, M. Mirshams, and M. Tayefi, "Active underactuation fault-tolerant backstepping attitude tracking control of a satellite with interval error constraints," Advanced Control for Applications, vol. 6, no. 3, 2024, Art. no. e215, https://doi.org/10.1002/adc2.215.
Volume 18, Issue 1
2025
Pages 78-91

  • Receive Date 19 January 2025
  • Revise Date 04 February 2025
  • Accept Date 02 March 2025
  • First Publish Date 02 March 2025