Attitude-orbit coupled sliding mode tracking control for spacecraft formation with event-triggered transmission

Fan, Ruichao; Chen, Xueqin; Liu, Ming; Cao, Xi‐Ren

doi:10.1016/j.isatra.2020.10.062

Cited by 16 publications

(4 citation statements)

References 30 publications

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“…S PACECRAFT attitude and orbit control technology play an essential role realizing most complex space missions. For example, spacecraft rendezvous and docking [1], [2], formation flying [3]- [5], and high-precision obstacle avoidance control [6], [7] put forward more and higher requirements for spacecraft attitude and orbit dynamics modeling and control. In order to simplify the design, most studies choose to model attitude and orbit separately.…”

Section: Introductionmentioning

confidence: 99%

“…In order to simplify the design, most studies choose to model attitude and orbit separately. However, due to the strong coupling of attitude trajectories, separate modeling will reduce the accuracy and fail to meet future aerospace requirements [6]. If the attitude and orbit motion of spacecraft can be controlled in an integrated way, it can greatly improve the accuracy and efficiency of spacecraft attitude and orbit control.…”

Section: Introductionmentioning

confidence: 99%

“…In this paper, it refer as "intrinsic". In the existing studies, the traditional proportionaldifferential (PD) control theory [18], [19] and sliding mode control theory [6], [20] have been applied to SE(3) . In addition, an adaptive timing terminal sliding mode control law based on convergence law was proposed in the literature [21] for the coupled spacecraft tracking maneuver problem with large inertial parameter uncertainties and external disturbances.…”

Section: Introductionmentioning

confidence: 99%

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Integrated Geometric Optimal Control of Spacecraft Attitude and Orbit Based on SE(3)

et al. 2023

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A model predictive convex programming (MPCP) on SE(3) parametrized by trigonometric series control is proposed in this paper, to solve the optimal control problem of spacecraft attitude orbit integration. Firstly, the geometric modeling of the spacecraft with six degrees of freedom for the attitude orbit integration is performed by the differential manifold SE(3) , which can effectively avoid the problems of ambiguity, receding winding, and singularity that occurs in the conventional methods for rigid body attitude description. Then, based on differential geometric theories, such as the variational principle, the left-invariant principle of Lie group, and the topology of Lie algebraic space, MPCP is applied to SE(3) . It can solve a class of optimization problems with process constraints and control input constraints during spacecraft flight. Furthermore, a control framework of trigonometric series is constructed, which is seamlessly integrated into MPCP to achieve smoother trajectory optimization control. Finally, the practicality and effectiveness of the proposed method are verified by numerical simulation.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Integrated Geometric Optimal Control of Spacecraft Attitude and Orbit Based on SE(3)

et al. 2023

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“…In Ref. [4], a coupled pose error dynamic model of 6-DOF spacecraft formations was established, based on which the authors devised a pose tracking law by employing the sliding mode control theory with an event-triggering strategy introduced to reduce the communication rate between the spacecraft. In Ref.…”

Section: Introductionmentioning

confidence: 99%

Homogeneous Finite-Time Pose Tracking of Leader–Following Spacecraft Formation Using a Twistor-Based Model

Guo,

Chen,

Zhang

et al. 2023

Electronics

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For integrated pose control of six-degree-of-freedom (6-DOF) leader–following spacecraft formations, the coupled relative pose between two spacecraft is described by a unified model in the framework of twistors, based on which a finite-time control law is devised for the 6-DOF dynamic system. Firstly, some necessary coordinate frames are defined, and then, relative 6-DOF dynamics of the follower spacecraft with respect to the desired frame are modeled by using twistors. Secondly, an integrated pose controller is designed for the 6-DOF formation that takes full advantage of homogeneous theory to guarantee finite-time stability. Finally, numerical simulations are carried out to validate the effectiveness of the proposed controller. Developing integrated 6-DOF formation control law based on twistors is more straightforward than conventional methods, and the finite-time algorithm achieves stronger robustness than asymptotic ones.

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Nonsingular Fast Terminal Sliding Mode Control for Integrated Attitude-Orbit Spacecraft Formation with Event-triggered Mechanism

Sun

Jia

2022

Lecture Notes in Electrical Engineering

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Attitude-orbit coupled sliding mode tracking control for spacecraft formation with event-triggered transmission

Cited by 16 publications

References 30 publications

Integrated Geometric Optimal Control of Spacecraft Attitude and Orbit Based on SE(3)

Integrated Geometric Optimal Control of Spacecraft Attitude and Orbit Based on SE(3)

Homogeneous Finite-Time Pose Tracking of Leader–Following Spacecraft Formation Using a Twistor-Based Model

Nonsingular Fast Terminal Sliding Mode Control for Integrated Attitude-Orbit Spacecraft Formation with Event-triggered Mechanism

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