Attitude Tracking Control for Rigid-Flexible Coupled Spacecraft with Guaranteed Performance Bounds

Xiao, Yan; Ruiter, Anton H. J. de; Ye, Dong; Sun, Zhiyong

doi:10.2514/1.g004535

Cited by 14 publications

(7 citation statements)

References 17 publications

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“…It should be noted that the diagonal values of J , namely J 0 = diag ([350, 270, 190])kg • m 2 , will be used to compute the control signal in order to show the robustness of the proposed controller against model uncertainty. In addition, four natural modes of the flexible appendages are considered in the simulation, and the main parameters of the flexible part are selected from [4], [6], [21]…”

Section: Simulation Resultsmentioning

confidence: 99%

“…Attitude stabilization and tracking problems for flexible-spacecraft have been studied extensively [9]. For instance, proportional derivative (PD) control [10] and PD plus feedforward compensation control [6] were proposed to investigate the attitude tracking control problem. The attitude stabilization problem was addressed in [11] and [12], where the requirement on the angular velocity was removed.…”

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confidence: 99%

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Agile Attitude Maneuvers with Active Vibration-suppression for Flexible-spacecraft

Zhang

Kong

Liu

et al. 2021

Preprint

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This paper addresses the agile attitude stabilization maneuver control of flexible-spacecraft using control moment gyros (CMGs) in the absence of modal information. Here, piezoelectric actuators are employed to actively suppress the vibration of flexible appendages. Both the attitude dynamics and the proposed robust controller are globally developed on the Special Orthogonal Group SO(3), avoiding ambiguities and singularities associated with other attitude representations. More specifically, an observer is first designed to estimate the modal information of vibration. A robust control law is developed by synthesizing a proportional derivative (PD) controller, an adaptive sliding mode controller, and an active vibration-suppression controller, which use the information of the estimated structural modes. The stability of the closed-loop system is proved using Lyapunov stability theory. Finally, numerical examples are performed to show the effectiveness of the proposed method.

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Section: Simulation Resultsmentioning

confidence: 99%

mentioning

confidence: 99%

Agile Attitude Maneuvers with Active Vibration-suppression for Flexible-spacecraft

Zhang

Kong

Liu

et al. 2021

Preprint

View full text Add to dashboard Cite

show abstract

“…By taking its 1st derivative w.r.t. time in order to allow for some convergence we end up with expression (26). Such a formulation allows formulating requirements for each single boom and each single mode.…”

Section: Control Implementationmentioning

confidence: 99%

“…Examples of applications of this kind of technology are solar sailing [19], active deorbiting of debris [17] and solar power generation [9]. Such lightweight structures triggered the development of controllers with specific performance bounds [26] and fixed maneuver times [5]. Additionally, flexibility in combination with liquid propellant is becoming more and more relevant [6,8].…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Controller Design for a Flexible Spacecraft

Gutierrez

Heidecker

2020

J Astronaut Sci

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This paper combines the nonlinear Udwadia-Kalaba control approach with the Assumed Mode Method to model flexible structures and derives an attitude controller for a spacecraft. The study case of this paper is a satellite with four flexible cantilever beams attached to a rigid central hub. Two main topics are covered in this paper. The first one is the formulation of the equation of motion and the second one is the nonlinear controller design. The combination of these two techniques is able to provide a controller that damps the vibration of a flexible structure while achieving the desired rigid-motion state.

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“…Compared to a single spacecraft, the multi-spacecraft formation system can provide better reliability and higher observation accuracy for Earth observation and deep space exploration. [1][2][3][4][5][6][7] Specifically, by adjusting the relative positions between the members, the baseline length of the formation system could be changed to adapt to different space tasks. [8][9][10] Therefore, the formation reconfiguration control problem has aroused widespread concern recently.…”

Section: Introductionmentioning

confidence: 99%

Feasibility analysis and saturation control for underactuated spacecraft formation reconfiguration in elliptic orbits

Shao,

Zhou,

Xiao

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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This work proposes a saturation control scheme for underactuated spacecraft formation reconfiguration in elliptic orbits without radial or along-track thrust. Firstly, the rank criterion method is applied to analyze the controllability and feasibility of formation reconfiguration by linearizing the linear time-varying dynamics to linear time-invariant ones. Based on the inherent coupling of the linear time-varying system, the underactuated error dynamics are presented for either underactuated case. Subsequently, the developed underactuated saturation controller can ensure that the time-varying system trajectory asymptotically converges to the specified configuration. The Lyapunov-based analysis presents the constraint conditions of controller parameters and the stable reconfiguration accuracy of the system states. Finally, numerical simulations for both underactuated scenarios are performed in the environment with J2 perturbation to verify the validity of the proposed underactuated control scheme.

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Attitude Tracking Control for Rigid-Flexible Coupled Spacecraft with Guaranteed Performance Bounds

Cited by 14 publications

References 17 publications

Agile Attitude Maneuvers with Active Vibration-suppression for Flexible-spacecraft

Agile Attitude Maneuvers with Active Vibration-suppression for Flexible-spacecraft

Nonlinear Controller Design for a Flexible Spacecraft

Feasibility analysis and saturation control for underactuated spacecraft formation reconfiguration in elliptic orbits

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