Low-order robust attitude control of an earth observation satellite

Valentin-Charbonnel, Catherine; Duc, Gilles; Ballois, Sandrine Le

doi:10.1016/s0967-0661(99)00006-4

Cited by 22 publications

(4 citation statements)

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“…The present work aims at presenting a novel model of SADM system together with its related disturbing signals in the TITOP framework. Charbonnel et al [21] presented an  ∞ attitude control design for an observation satellite by taking into account both reaction wheel and SADM disturbances. Cumer et al [22] provided a minimal LFT form of a flexible spacecraft with a SADM.…”

Section: Background and Motivationmentioning

confidence: 99%

Integrated modeling of microvibrations induced by Solar Array Drive Mechanism for worst-case end-to-end analysis and robust disturbance estimation

Sanfedino

Alazard

Preda

et al. 2022

Mechanical Systems and Signal Processing

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Section: Background and Motivationmentioning

confidence: 99%

Integrated modeling of microvibrations induced by Solar Array Drive Mechanism for worst-case end-to-end analysis and robust disturbance estimation

Sanfedino

Alazard

Preda

et al. 2022

Mechanical Systems and Signal Processing

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“…The present work aims at presenting a novel model of SADM system together with its related disturbing signals in the TITOP framework. Charbonnel et al [19] presented an H ∞ attitude control design for an observation satellite by tacking into account both reaction wheel and SADM disturbances. Cumer et al [20] provided a minimal LFT form of a flexible spacecraft with a SADM.…”

Section: Background and Motivationmentioning

confidence: 99%

Integrated modelling of microvibrations induced by Solar Array Drive Mechanism for worst-case end-to-end analysis and robust disturbance estimation

Sanfedino,

Alazard,

Preda

et al. 2021

Preprint

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Modern and future observation Space missions face increasingly more demanding pointing performance requirements. This is accompanied with the development of larger lightweight flexible structures. This paper outlines a methodology for modeling a generic multi-body flexible spacecraft in an end-to-end fashion within the Two-Inputs Two-Outputs Port framework: from disturbance all the way to pointing performance by tacking into account all the uncertainties of each sub-system. A particular focus is dedicated to a novel generic model for Solar Drive Array Mechanisms and its harmonic disturbances produced by the micro-stepping driver and the gearbox imperfections. The proposed model is validated with the on-board telemetries of a European spacecraft. Moreover this paper shows how the proposed model-based approach can be easily used for control design and closed-loop robust performance analysis. Worst-case scenarios of mechanical parameters combination are investigated to provide robust performance certificate of the reference study case. A Linear Parameter-Varying observer, scheduled by the solar array rotor angle, is finally proposed in order to estimate the disturbance torques induced by the gearbox imperfections just using the measurements coming from a classical attitude control system: a star tracker and a gyrometer.

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“…The next step of using the optimisation algorithm to return the final controller was then carried out, to get a robustly stabilising controller. The problem with this procedure is that the controller order is very high [14].…”

Section: B Flexible Spacecraft Attitude Controller Designmentioning

confidence: 99%

Command Shaped Robust Control of a Flexible Spacecraft

Butt¹

2017

JOACE

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In this paper a model of a hypothetical flexible spacecraft that resembles French multi mission satellite SPOT is selected. This model represents a multivariable system that is difficult to control due to strong cross couplings. In order to get a good insight, initially analysis of the model is carried out from the perspective of control design challenge peculiar to this system. Later a systematic multivariable robust controller is designed based on  H Loop Shaping Design Procedure. The designed controller is able to stabilize the overall system but is unable to minimize oscillations in structure that cause fine pointing issues. To remove the problem of small amplitude oscillations for this design, input command shaping technique is applied that is able to effectively minimize oscillations. Finally, robustness and performance of the designed controller is demonstrated through numerical simulations.  Index Terms-Command shaping, flexibility, robust control, spacecraft, loop shaping design I.

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Low-order robust attitude control of an earth observation satellite

Cited by 22 publications

References 0 publications

Integrated modeling of microvibrations induced by Solar Array Drive Mechanism for worst-case end-to-end analysis and robust disturbance estimation

Integrated modeling of microvibrations induced by Solar Array Drive Mechanism for worst-case end-to-end analysis and robust disturbance estimation

Integrated modelling of microvibrations induced by Solar Array Drive Mechanism for worst-case end-to-end analysis and robust disturbance estimation

Command Shaped Robust Control of a Flexible Spacecraft

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