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This paper proposes adaptive fuzzy PD+ based controller for the attitude maneuver of rigid spacecraft. Based on the error of the system, the adaptive fuzzy PD+ based controller applies adaptive fuzzy algorithm to modify the gains of PD+ attitude controller online. The advantage of the adaptive fuzzy PD+ based controller is presented in simulation results.
The control problem of spacecraft eigenaxis maneuver in the presence of parametric uncertainty and external disturbance is addressed in this paper. Modified Rodrigues parameters (MRPs) are utilized as the attitude parameters for the non-redundancy. An eigenaxis maneuver control law with feedback and feed-forward terms is presented for the nominal system. The transient response of close loop system...
This paper aims to present an improved adaptive sliding mode control (ASMC) design for rigid spacecraft attitude maneuvers. An adaptive scheme is proposed for the switching gain calculation when the upper bound of the system uncertainty is unknown in advance. Unlike existing ASMC design, which may result in an over-adaptation of the upper bound when the initial system trajectory is located far from...
This paper aims to address the robust control problem of rigid spacecraft attitude maneuvers in the presence of inertia matrix uncertainty and external disturbance. A back-stepping based adaptive sliding mode control (B-ASMC) design is proposed as a solution, where the upper bounds of the parametric uncertainty and disturbance are not required in advance. Compared to current adaptive sliding mode...
In this paper, the attitude control problem for uncertain spacecraft under angular velocity constraint is addressed. Both parametric uncertainty and external disturbance are considered in the spacecraft's dynamics. The spacecraft's attitude is represented by modified Rodrigues parameter (MRP) for its non-redundancy. A time-varying sliding mode control (TVSMC) algorithm is derived for attitude control...
In this paper, the attitude tracking problem of rigid spacecraft without inertial or relative angular velocity measurements is investigated. The minimal attitude description, the modified Rodrigues parameters (MRPs), are utilized as the attitude parameters for the non-redundancy. The inherent passivity of the system describing the attitude tracking motion of the spacecraft is exploited. Then an attitude...
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