The attitude tracking control problem of a rigid spacecraft with actuator saturation is investigated
in this paper. A finite-time attitude tracking control scheme is presented by incorporating sliding mode control
(SMC) and adaptive technique. Specifically, a novel time-varying sliding mode manifold is first developed that
aims at regulating the attitude tracking error to equilibrium point within a certain finite time. Moreover, it can
be specified a priori by the designer according to the mission requirement. Subsequently, an adaptive controller is
derived by using the SMC in conjunction with adaptive technique. The designed controller is capable of ensuring
that the state trajectories reach to sliding regime within a finite time, and hence that attitude tracking error can
converge to zero in a finite time with the aid of the developed sliding dynamics, despite the presence of exogenous
disturbances, unknown inertia properties and saturation nonlinearities. Finally, the simulation experiments are
carried out to demonstrate the effectiveness of the proposed control scheme.
LIU Yueyang (刘岳洋), HU Qinglei (胡庆雷), GUO Lei (郭雷)
. Finite-Time Attitude Tracking Control of Spacecraft with Actuator Saturation[J]. Journal of Shanghai Jiaotong University(Science), 2018
, 23(5)
: 650
-656
.
DOI: 10.1007/s12204-018-1994-x
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