Finite‐time attitude synchronisation for multiple spacecraft

Lyu, Jianting; Qin, Jiahu; Ma, Qiao; Zheng, Wei Xing; Kang, Yu

doi:10.1049/iet-cta.2015.1136

Cited by 36 publications

(29 citation statements)

References 30 publications

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“…Different control techniques have been proposed in the literature for automated rendezvous and docking, including H ∞ control [33], Riccati equation techniques [34], [35], graph theory [36], feedback-linearization-based approach [37]. In the last years, special attention has been reserved to the adoption of model predictive control (MPC) as control techniques for autonomous rendezvous and docking (ARVD), due to its capability of dealing with the constraints that typically characterize this maneuver, both in terms of relative position and velocity.…”

Section: Control Algorithmsmentioning

confidence: 99%

“Flyable” Guidance and Control Algorithms for Orbital Rendezvous Maneuver

Capello

Dabbene

Guglieri

et al. 2018

SICE Journal of Control, Measurement, and System Integration

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: Rendezvous orbital maneuvers are planned operations which intend to make two spacecraft meet, while avoiding collisions. Aspects such as trajectory safety and robustness, as well as obstacle avoidance, are fundamental for the mission success. The aim of this paper is to provide an overview of some recent algorithms for guidance and control systems, and also their combined exploitation, which can provide significant enhancements. This overview focuses on those algorithms that are characterized by key selected features: the discussed schemes guarantee low computational effort, low fuel consumption, and high safety and robustness. Different experimental setups, which can be used to evaluate the performance of the considered algorithms, are also taken into account and presented.

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Section: Control Algorithmsmentioning

confidence: 99%

“Flyable” Guidance and Control Algorithms for Orbital Rendezvous Maneuver

Capello

Dabbene

Guglieri

et al. 2018

SICE Journal of Control, Measurement, and System Integration

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show abstract

“…As compared with asymptotic control laws, finite‐time control schemes can demonstrate some superior properties, such as higher precision control performance, better disturbance rejection ability, and faster convergence rate (near the equilibrium point). Thus, finite‐time control for second‐order multiagent systems has been studied by some researchers using the terminal sliding mode method, the technique of “adding a power integrator,” and the homogeneity theorem …”

Section: Introductionmentioning

confidence: 99%

Fixed‐time output‐feedback consensus tracking control for second‐order multiagent systems

Zou

2019

Intl J Robust & Nonlinear

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Summary This paper is concerned with the problem of fixed‐time consensus tracking control for a class of second‐order multiagent systems under an undirected communication graph. A distributed output‐feedback fixed‐time consensus tracking control scheme is proposed to make the states of all individual agents simultaneously track a time‐varying reference state even when the reference state is available only to a subset of the group members and only output measurements are available for feedback. Homogeneous Lyapunov function and homogeneity property are employed to show that the control scheme can guarantee the consensus tracking errors converging the origin in finite time which is bounded by a fixed constant independent of initial conditions. Numerical simulations are carried out to demonstrate the effectiveness of the proposed control law.

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“…Therefore, the development of a finite‐time attitude coordination control scheme for multiple spacecraft is highly desirable. The design methods for the finite‐time attitude coordination control problem include the terminal sliding mode method, the technique of “adding a power integrator,” and the homogeneity theorem …”

Section: Introductionmentioning

confidence: 99%

“…Based on the homogeneity theorem, a bounded finite‐time attitude controller was proposed for multiple rigid spacecraft with a leader‐follower architecture . By using the homogeneous method, a finite‐time attitude synchronization control scheme was developed for multiple spacecraft under a directed communication topology . With the aid of the homogeneity theorem and the finite‐time observer derived in Zou, a distributed velocity‐free attitude coordination control law was proposed for spacecraft formations …”

Section: Introductionmentioning

confidence: 99%

“…The main contributions of this work are stated as follows. As compared with the existing results, the proposed control scheme can guarantee that the attitudes of a group of spacecraft simultaneously track a time‐varying reference attitude in finite time and the upper bound of this finite time is independent of initial conditions. By introducing some new lemmas, the limitation on the power in the existing control schemes based on the technique of adding a power integrator is relaxed in this work. Different from the other works, the backstepping method together with the technique of adding a power integrator are used to design the fixed‐time control law, and the implementation of the proposed control scheme does not have the algebraic loop problem as existed in the work of Zuo and Tian et al …”

Section: Introductionmentioning

confidence: 99%

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Distributed fixed‐time attitude coordination control for multiple rigid spacecraft

Zou

Fan

2019

Intl J Robust & Nonlinear

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Summary In this paper, the fixed‐time attitude coordination control for multiple rigid spacecraft under an undirected communication graph is investigated. By using the backstepping technique, the distributed fixed‐time observer, and the method of “adding a power integrator,” a distributed fixed‐time attitude coordination control law is designed for a group of spacecraft. The proposed control scheme is nonsingular and can guarantee a group of rigid spacecraft simultaneously tracking a common desired attitude within fixed time even when the time‐varying reference attitude is available only to a subset of the group members. Rigorous analysis is provided to show that the attitude consensus tracking errors can converge to the origin in finite time which is bounded by a fixed constant independent of initial conditions. Numerical simulations are carried out to demonstrate the effectiveness of the proposed control law.

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Finite‐time attitude synchronisation for multiple spacecraft

Cited by 36 publications

References 30 publications

“Flyable” Guidance and Control Algorithms for Orbital Rendezvous Maneuver

“Flyable” Guidance and Control Algorithms for Orbital Rendezvous Maneuver

Fixed‐time output‐feedback consensus tracking control for second‐order multiagent systems

Distributed fixed‐time attitude coordination control for multiple rigid spacecraft

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