H-infinity control of an Earth observation satellite

Ballois, Sandrine Le; Duc, Gilles

doi:10.2514/3.21667

Cited by 29 publications

(4 citation statements)

References 10 publications

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“…The spacecraft is described as a rigid body with three flexible appendages, and the attitude dynamics is governed by the following differential equations [14,31]…”

Section: Attitude Dynamics Of the Flexible Spacecraftmentioning

confidence: 99%

“…Alternatively, a controller with a simple structure and low orders is more desirable for real case applications [29]. The simple state or output feedback controller based on H∞ control design methodology has been used in space missions [30][31], since it has a PD-like structure and clear physical meaning. Besides, the problem of spacecraft parameter uncertainties has been widely addressed, and a commonly-used methodology is to assume that the uncertain parameters, typically the moments of inertia, always consist of the nominal component and the uncertain one [4, 6, 12-16, 18, 25, 27].…”

Section: Introductionmentioning

confidence: 99%

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Multi-objective integrated robust H∞ control for attitude tracking of a flexible spacecraft

Chu

Ma³

et al. 2018

Acta Astronautica

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This paper investigates the multi-objective attitude tracking problem of a flexible spacecraft in the presence of disturbances, parameter uncertainties and imprecise collocation of sensors and actuators. An integrated robust H∞ controller, including an output feedback component and a feedforward component, is proposed, and its gains are calculated by solving Linear Matrix Inequalities. The output feedback component stabilizes the integrated control system while the feedforward component can drive the attitude motion to track the desired angles. The system robustness against disturbances, parameter uncertainties and imprecise collocation is addressed by the H∞ approach and convex optimization. Numerical simulations are finally provided to assess the performance of the proposed controller.

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“…The spacecraft is described as a rigid body with three flexible appendages, and the attitude dynamics is governed by the following differential equations [14,31]…”

Section: Attitude Dynamics Of the Flexible Spacecraftmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Multi-objective integrated robust H∞ control for attitude tracking of a flexible spacecraft

Chu

Ma³

et al. 2018

Acta Astronautica

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“…In [10,11], a series of variable structure control schemes have been provided systematically for vibration suppression problems. H ∞ control has been used in ACS design in [12,13] where external disturbance and model uncertainty are considered. An H ∞ multi-objective controller based on the Linear Matrix Inequality (LMI) framework, is designed for flexible spacecraft in [14].…”

Section: Introductionmentioning

confidence: 99%

An anti-disturbance PD control scheme for attitude control and stabilization of flexible spacecrafts

2011

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This paper studies the attitude control problem of spacecrafts with flexible appendages. It is well known that the unwanted vibration modes, model uncertainty and space environmental disturbances may cause degradation of the performance of attitude control systems for a flexible spacecraft. In this paper, the vibration from flexible appendages is modeled as a derivative-bounded disturbance to the attitude control system of the rigid hub. A disturbance-observer-based control (DOBC) is formulated for feedforward compensation of the elastic vibration. The model uncertainty and space environmental disturbances as well as other noises are merged into an "equivalent" disturbance. We design a composite controller with a hierarchical architecture by combining DOBC and PD control, where DOBC is used to reject the vibration effect from the flexible appendages. Numerical simulations are performed to demonstrate that by using the composite hierarchical control law, disturbances can be effectively attenuated and the robust dynamic performances be enhanced.

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“…∞ control has been used in attitude control systems design in [9,10] where external disturbance and model uncertainty are considered. An ∞ multiobjective controller based on the linear matrix inequality (LMI) framework is designed for flexible spacecraft in [11].…”

Section: Introductionmentioning

confidence: 99%

H∞Control for Flexible Spacecraft with Time-Varying Input Delay

Zhang

2013

Mathematical Problems in Engineering

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This paper is concerned withH∞control problem for flexible spacecraft with disturbance and time-varying control input delay. By constructing an augmented Lyapunov functional with slack variables, a new delay-dependent state feedback controller is obtained in terms of linear inequality matrix. These slack variables can make the design more flexible, and the resultant design also can guarantee the asymptotic stability andH∞attenuation level of closed-loop system. The effectiveness of the proposed design method is illustrated via a numerical example.

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H-infinity control of an Earth observation satellite

Cited by 29 publications

References 10 publications

Multi-objective integrated robust H∞ control for attitude tracking of a flexible spacecraft

Multi-objective integrated robust H∞ control for attitude tracking of a flexible spacecraft

An anti-disturbance PD control scheme for attitude control and stabilization of flexible spacecrafts

H∞Control for Flexible Spacecraft with Time-Varying Input Delay

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