Flexible Spacecraft Vibration Suppression Using PWPF Modulated Input Component Command and Sliding Mode Control

Hu, Qinglei; Ma, Guangfu

doi:10.1111/j.1934-6093.2007.tb00300.x

Cited by 16 publications

(14 citation statements)

References 22 publications

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“…Ebarahimi et al [8] developed a minimum-time optimal control law for a flexible satellite using the assumed modes method for the flexible appendage. Hu and Ma [9] presented a dual-stage control system design method for the rotational maneuver and vibration stabilization of a satellite with flexible appendages. Kim et al [10] defined the efficient dynamic model of a satellite with flexible solar panels by using the component mode synthesis technique.…”

Section: Introductionmentioning

confidence: 99%

Optimal Design of a High-Agility Satellite with Composite Solar Panels

Kim¹,

Kim²,

Kim³

et al. 2016

International Journal of Aeronautical and Space Sciences

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This paper defines mode shape function of a composite solar panel assumed as Kirchhoff-Love plate for considering a torsional mode of composite solar panel. It then goes on to define dynamic model of a high-agility satellite considering the flexibility of composite solar panel as well as stiffness of a solar panel's hinge using Lagrange's theorem, Ritz method and the mode shape function. Furthermore, this paper verifies the validity of dynamic model by comparing numerical results from the finite element analysis. In addition, this paper performs a dynamic response analysis of a rigid satellite which includes only natural modes for solar panel's hinges and a flexible satellite which includes not only natural modes of solar panel's hinges, but also structural modes of composite solar panels. According to the results, we confirm that the torsional mode of solar panel should be considered for the structural design of high-agility satellite. Finally, we performed optimization of high-agility satellite for minimizing mass with solar panel's area limit using the defined dynamic model. Consequently, we observed that the defined dynamic model for a high-agility satellite and result of the optimal design are very useful not only because of their optimal structural design but also because of the dynamic analysis of the satellite.

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Section: Introductionmentioning

confidence: 99%

Optimal Design of a High-Agility Satellite with Composite Solar Panels

Kim¹,

Kim²,

Kim³

et al. 2016

International Journal of Aeronautical and Space Sciences

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“…One of several ways to reduce residual vibrations in input shaping control [1][2] is an open-loop control technique that can reduce residual vibrations of undamped or under-damped systems by convolving a sequence of impulses with a desired command. This, however, lacks intrinsic robustness to modeling errors due to its open-loop control characteristics.…”

Section: Introductionmentioning

confidence: 99%

On a Simplified Residual Vibration Ratio Function for Input Shaping Control

Kang¹,

Kwak²

2012

Asian Journal of Control

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In the literature of input shaping control, two kinds of residual vibration ratio function have been introduced for evaluating the robustness of input shaping control to modeling error. Also, two types of derivative constraints for the residual vibration ratio function have been used for suppressing residual vibration under the condition of having some modeling errors in natural frequency and damping ratio. In this paper, a simplified residual vibration ratio function is presented, which is more convenient to use than the conventional function, and the equivalence of two derivative constraints for the simplified residual vibration ratio function is shown mathematically. The validity of the assertion is demonstrated by means of simulation and experimental studies.

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“…In [7], a dual-stage control system design method for the rotational maneuver and vibration stabilization of a flexible spacecraft is presented. In [7], a dual-stage control system design method for the rotational maneuver and vibration stabilization of a flexible spacecraft is presented.…”

Section: Introductionmentioning

confidence: 99%

“…Recent papers have discussed nonlinear robust methodologies for the control of flexible mechanical systems. In [7], a dual-stage control system design method for the rotational maneuver and vibration stabilization of a flexible spacecraft is presented. The design of attitude controller was based on sliding mode control (SMC) theory leading to a discontinuous control law.…”

Section: Introductionmentioning

confidence: 99%

Robust attitude and vibration control of a nonlinear flexible spacecraft

Malekzadeh¹,

Naghash²,

Talebi

2010

Asian Journal of Control

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In this paper, the problem of attitude control of a three dimension nonlinear flexible spacecraft is investigated. Two nonlinear controllers are presented. The first controller is based on dynamic inversion, while the second approach is composed of dynamic inversion and -synthesis schemes. It is assumed that only three torques in three directions on the hub are used. Actuator saturation is also considered in the design of controllers. To evaluate the performance of the proposed controllers, an extensive number of simulations on a nonlinear model of the spacecraft are performed. The performances of the proposed controllers are compared in terms of nominal performance, robustness to uncertainties, vibration suppression of panel, sensitivity to measurement noise, environmental disturbance and nonlinearity in large maneuvers. Simulation results confirm the ability of the proposed controller in tracking the attitude trajectory while suppressing the panel vibration. It is also verified that the perturbations, environment disturbances and measurement errors have only slight effects on the tracking and suppression performances.

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Flexible Spacecraft Vibration Suppression Using PWPF Modulated Input Component Command and Sliding Mode Control

Cited by 16 publications

References 22 publications

Optimal Design of a High-Agility Satellite with Composite Solar Panels

Optimal Design of a High-Agility Satellite with Composite Solar Panels

On a Simplified Residual Vibration Ratio Function for Input Shaping Control

Robust attitude and vibration control of a nonlinear flexible spacecraft

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