Renyong Zhang1, Caisheng Wei2, *, Zeyang Yin3, *
CMES-Computer Modeling in Engineering & Sciences, Vol.122, No.1, pp. 89-107, 2020, DOI:10.32604/cmes.2020.07985
Abstract 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. More >
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