Purpose
The purpose of this paper is to propose an adaptive robust controller for coupled attitude and orbit control of rigid spacecraft based on dual quaternion in the presence of external disturbances and model uncertainties.
Design/methodology/approach
First, based on dual quaternion, a theoretical model of the relative motion for rigid spacecraft is introduced. Then, an adaptive robust controller which can realize coordinated control of attitude and orbit is designed in the existence of external disturbances and model uncertainties.
Findings
This paper takes advantage of the Lyapunov function which can guarantee the asymptotic stabilization of the whole system in the existence of parameters uncertainties. Simulation results show that the proposed controller is feasible and effective.
Originality/value
This paper proposes a coupled attitude and orbit adaptive robust controller based on dual quaternion. Simulation results demonstrate that the proposed controller can achieve higher control performance in the presence of parameters uncertainties.
For the two-satellite formation, the relative motion and attitude determination algorithm is a key component that affects the flight quality and mission efficiency. The relative status determination algorithm is proposed based on the Extended Kalman Filter (EKF) and the system state optimal estimate linearization. Aiming at the relative motion of the spacecraft formation navigation problem, the spacecraft relative kinematics and dynamics model are derived from the dual quaternion in the algorithm. Then taking advantage of EKF technique, combining with the dual quaternion integrated dynamic models, considering the navigation algorithm using the fusion measurement by the gyroscope and star sensors, the relative status determination algorithm is designed. At last the simulation is done to verify the feasibility of the algorithm. The simulation results show that the EKF algorithm has faster convergence speed and higher accuracy.
Event‐triggered coordinated attitude control problem for satellite formation under switching topology is investigated in this article. First, triggering function with state error is designed to adjust update period of controller. Event is triggered, state information is sampled, and controller is updated if and only if triggering condition is satisfied, while controller in nontriggering time uses state information of triggering time. Then, in the existence of model uncertainties, distributed adaptive attitude controller based on event‐triggered strategy is proposed for satellite formation with leader‐follower architecture. Under directed switching graph, formation system is proved to be asymptotical convergence by Lyapunov stability theory, and inter‐event time interval is given to avoid Zeno behavior. At last, simulation results show that the proposed event‐triggered adaptive attitude controller can reduce execution frequency of control tasks, as well as ensure control performance of cluster system.
In order to investigate coordinated orbit control problem for large-scale cluster flight spacecraft, a distributed orbital containment control algorithm is proposed for spacecraft cluster flight system with multiple leaders. At first, a general distributed orbital containment control strategy for largescale cluster spacecraft system is given, so that all followers are driven to the convex hull formed by leaders. Then the constraints of convergence and convergence rate of cluster spacecraft system on control gains and information topology are investigated. Specifically, the control gains which achieve maximal convergence rate are analyzed. Furthermore, two kinds of cell partitions from graph theory are employed to investigate the influence of information topology on steady states of followers, which provides theoretical basis for collision avoidance design. Finally, simulation results show that the designed information topology could meet the requirements of large-scale cluster system, and followers belonging to the same cell have the same steady states. INDEX TERMS Large-scale cluster, orbital control, multiple leaders, containment control, graph theory, topology design.
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