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Adaptive Quasi Fixed-Time Orbit Control Around Asteroid with Performance Guarantees

Renyong Zhang1, Caisheng Wei2, *, Zeyang Yin3, *

1Technology and Engineering Center for Space Utilization, Chinese Academy of Sciences, Beijing, 100094, China.
2 School of Aeronautics and Astronautics, Central South University, Changsha, 410083, China.
3 School of Astronautics, Northwestern Polytechnical University, Xi’an, 710072, China.

* Corresponding Authors: Caisheng Wei. Email: ;
   Zeyang Yin. Email: .

(This article belongs to this Special Issue: Nonlinear Computational and Control Methods in Aerospace Engineering)

Computer Modeling in Engineering & Sciences 2020, 122(1), 89-107.


This paper investigates a novel quasi fixed-time orbit tracking control method for spacecraft around an asteroid in the presence of uncertain dynamics and unknown uncertainties. To quantitatively characterize the transient and steady-state responses of orbit tracking error system, a continuous performance function is devised via using a quartic polynomial. Then, integrating backstepping control technique and barrier Lyapunov function leads to a quasi fixed-time convergent orbit tracking controller without using any fractional state information and symbolic functions. Finally, two groups of illustrative examples are employed to test the effectiveness of the proposed orbit control method.


Cite This Article

Zhang, R., Wei, C., Yin, Z. (2020). Adaptive Quasi Fixed-Time Orbit Control Around Asteroid with Performance Guarantees. CMES-Computer Modeling in Engineering & Sciences, 122(1), 89–107.

This work is licensed under a Creative Commons Attribution 4.0 International License , which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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