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04 December 2021
Switching LPV control for electromagnetic formation flying on highly elliptical orbit
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The electromagnetic force generated by the interaction of electromagnetic coils can be used to replace the conventional propellant consumption mode in close relative motion control, thereby promoting the application of formation flight technology for long-term and continuous space missions. Herein, a hysteresis-switching logic-based switching linear parameter varying (LPV) controller synthesis technique with guaranteed performance for electromagnetic formation flying on a highly elliptical orbit is proposed. First, considering that the relative dynamics model of an elliptical orbit is characterized by time-varying uncertainty, the LPV model is described. By introducing switching LPV controllers among different scheduled parameter subsets, conservativeness can be reduced. Second, the system modeling error, the uncertainty caused by a simplified electromagnetic coil model, and external disturbance are considered to derive switching LPV controller synthesis conditions based on the guaranteed H∞ performance. Derivation analysis shows that the proposed switching LPV controller not only ensures the robustness of the system against uncertainties, but also realizes the control input constraints. Finally, numerical simulations and comparative analyses are performed to demonstrate the effectiveness and advantages of the proposed control method.
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Switching LPV control for electromagnetic formation flying on highly elliptical orbit
Abstract
The electromagnetic force generated by the interaction of electromagnetic coils can be used to replace the conventional propellant consumption mode in close relative motion control, thereby promoting the application of formation flight technology for long-term and continuous space missions. Herein, a hysteresis-switching logic-based switching linear parameter varying (LPV) controller synthesis technique with guaranteed performance for electromagnetic formation flying on a highly elliptical orbit is proposed. First, considering that the relative dynamics model of an elliptical orbit is characterized by time-varying uncertainty, the LPV model is described. By introducing switching LPV controllers among different scheduled parameter subsets, conservativeness can be reduced. Second, the system modeling error, the uncertainty caused by a simplified electromagnetic coil model, and external disturbance are considered to derive switching LPV controller synthesis conditions based on the guaranteed H∞ performance. Derivation analysis shows that the proposed switching LPV controller not only ensures the robustness of the system against uncertainties, but also realizes the control input constraints. Finally, numerical simulations and comparative analyses are performed to demonstrate the effectiveness and advantages of the proposed control method.
References(35)
Elias, L. M., Kwon, D. W., Sedwick, R. J., Miller, D. W. Electromagnetic formation flight dynamics including reaction wheel gyroscopic stiffening effects. Journal of Guidance, Control, and Dynamics, 2007, 30(2): 499–511.
Huang, H., Cai, W. W., Yang, L. P. 6-DOF formation keeping control for an invariant three-craft triangular electromagnetic formation. Advances in Space Research, 2020, 65(1): 312–325.
Miller, D. W., Ahsun, U., Ramirez-Riberos, J. L. Control of electromagnetic satellite formations in near-Earth orbits. Journal of Guidance, Control, and Dynamics, 2010, 33(6): 1883–1891.
Xu, Z., Shi, P., Zhao, Y. Adaptive control for two-spacecraft electromagnetic formation keeping. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(12): 2302–2308. (in Chinese)
Zeng, G. Q., Hu, M. Finite-time control for electromagnetic satellite formations. Acta Astronautica, 2012, 74: 120–130.
Huang, X. L., Zhang, C., Lu, H. Q., Li, M. M. Adaptive reaching law based sliding mode control for electromagnetic formation flight with input saturation. Journal of the Franklin Institute, 2016, 353(11): 2398–2417.
Zhang, Y., Shi, P., Zhang, H., Zhao, Y. A robust coordinated control method for hovering of electromagnetic spacecraft formation. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(2): 388–397. (in Chinese)
Sun, X. Z., Xia, D. W., Chen, W. D., Hao, Y., Mantey, K. A., Zhao, H. Dual quaternion based dynamics modeling for electromagnetic collocated satellites of diffraction imaging on geostationary orbit. Acta Astronautica, 2020, 166: 52–58.
Qi, D. W., Yang, L. P., Zhang, Y. W., Cai, W. W. Indirect robust suboptimal control of two-satellite electromagnetic formation reconfiguration with geomagnetic effect. Advances in Space Research, 2019, 64(11): 2331–2344.
Wei, C. Z., Park, S. Y., Park, C. Optimal H∞ robust output feedback control for satellite formation in arbitrary elliptical reference orbits. Advances in Space Research, 2014, 54(6): 969–989.
Rugh, W. J., Shamma, J. S. Research on gain scheduling. Automatica, 2000, 36(10): 1401–1425.
Shamma, J. S., Cloutier, J. R. Gain-scheduled missile autopilot design using linear parameter varying transformations. Journal of Guidance, Control, and Dynamics, 1993, 16(2): 256–263.
Scherer, C., Gahinet, P., Chilali, M. Multiobjective output-feedback control via LMI optimization. IEEE Transactions on Automatic Control, 1997, 42(7): 896–911.
Apkarian, P., Adams, R. J. Advanced gain-scheduling techniques for uncertain systems. IEEE Transactions on Control Systems Technology, 1998, 6(1): 21–32.
He, T. Y., Al-Jiboory, A. K., Zhu, G. G., Swei, S. S. M., Su, W. H. Application of ICC LPV control to a blendedwing-body airplane with guaranteed H∞ performance. Aerospace Science and Technology, 2018, 81: 88–98.
Nie, L., Cai, B., Lu, S. G., Qin, H., Zhang, L. X. Finitetime switched LPV control of quadrotors with guaranteed performance. Journal of the Franklin Institute, 2021, 358(14): 7032–7054.
Nagashio, T., Kida, T., Hamada, Y., Ohtani, T. Robust two-degrees-of-freedom attitude controller design and flight test result for engineering test satellite-VIII spacecraft. IEEE Transactions on Control Systems Technology, 2014, 22(1): 157–168.
Wang, S., Pfifer, H., Seiler, P. Robust synthesis for linear parameter varying systems using integral quadratic constraints. Automatica, 2016, 68: 111–118.
Al-Hajjar, A. M. H., Swei, S. S. M., Zhu, G. G. Hard constrained LPV virtual control with application to flutter suppression of a smart airfoil. International Journal of Control, Automation and Systems, 2020, 18(5): 1215–1228.
Qu, S., He, T. Y., Zhu, G. G. Engine EGR valve modeling and switched LPV control considering nonlinear dry friction. IEEE/ASME Transactions on Mechatronics, 2020, 25(3): 1668–1678.
Lu, B., Wu, F. Switching LPV control designs using multiple parameter-dependent Lyapunov functions. Automatica, 2004, 40(11): 1973–1980.
Zhao, Y. Y., Yang, J. Y., Lei, Z. D. H∞ Guaranteed cost control for LPV systems subject to the gain constraint. Asian Journal of Control, 2014, 16(2): 609–616.
Llorente, J. S., Agenjo, A., Carrascosa, C., de Negueruela, C., Mestreau-Garreau, A., Cropp, A., Santovincenzo, A. PROBA-3: Precise formation flying demonstration mission. Acta Astronautica, 2013, 82(1): 38–46.
Lei, B. Y., Shi, P., Wen, C. X., Zhao, Y. S. Gainscheduling attitude control for complex spacecraft based on HOSVD. Journal of Dynamic Systems, Measurement, and Control, 2019, 141(3): 034503.
Apkarian, P. Nonsmooth µ-synthesis. International Journal of Robust and Nonlinear Control, 2011, 21(13): 1493–1508.
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Acknowledgements
This study was supported by the National Natural Science Foundation of China (No. 11572019) and the Natural Science General Fund of Shanghai (No. 19ZR1453300).
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