Design and implementation of robust symmetric attitude controller for ETS-VIII spacecraft

Nagashio, Tomoyuki; Kida, Takashi; Ohtani, Takashi; Hamada, Yoshiro

doi:10.1016/j.conengprac.2009.05.003

Cited by 51 publications

(14 citation statements)

References 16 publications

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“…The satellite has four large flexible appendages including a pair of deployable antenna reflectors and a pair of solar array panels [19]. The solar panels rotate around the pitch axis so that they continually face the sun; the solar panel rotation of the satellite can cause a maximum 25% change for the structure parameters [20]. Consequently, the satellite can be studied as an LTV system.…”

Section: Large Flexible Satellite Ets-viiimentioning

confidence: 99%

Time-varying modal parameters identification of large flexible spacecraft using a recursive algorithm

Ni¹,

Wu²,

Wu³

2016

International Journal of Aeronautical and Space Sciences

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In existing identification methods for on-orbit spacecraft, such as eigensystem realization algorithm (ERA) and subspace method identification (SMI), singular value decomposition (SVD) is used frequently to estimate the modal parameters. However, these identification methods are often used to process the linear time-invariant system, and there is a lower computation efficiency using the SVD when the system order of spacecraft is high. In this study, to improve the computational efficiency in identifying time-varying modal parameters of large spacecraft, a faster recursive algorithm called fast approximated power iteration (FAPI) is employed. This approach avoids the SVD and can be provided as an alternative spacecraft identification method, and the latest modal parameters obtained can be applied for updating the controller parameters timely (e.g. the self-adaptive control problem). In numerical simulations, two large flexible spacecraft models, the Engineering Test Satellite-VIII (ETS-VIII) and Soil Moisture Active/Passive (SMAP) satellite, are established. The identification results show that this recursive algorithm can obtain the time-varying modal parameters, and the computation time is reduced significantly.

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Section: Large Flexible Satellite Ets-viiimentioning

confidence: 99%

Time-varying modal parameters identification of large flexible spacecraft using a recursive algorithm

Ni¹,

Wu²,

Wu³

2016

International Journal of Aeronautical and Space Sciences

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“…In our experiment, the controller is optimized for the disturbance attenuation by minimizing the H ∞ norm of the closed-loop system. On the other hand, the feedforward controller is designed as a gain scheduling controller by applying a model matching method to the LPV system (Apkarian et al 1995, Nagashio et al 2010. In order to optimize each controller for all δ, we utilize the fact that M (δ) is bounded for all δ and given by the convex decomposition as…”

Section: Controller Designmentioning

confidence: 99%

“…Therefore, the attitude control system must guarantee robust stability against above mentioned higher vibration modes and modal parameter uncertainties for a linear parameter varying (LPV), multi-input multioutput (MIMO) system. From this viewpoint, the authors have proposed several control methods (Hamada et al 2007, Ohtani et al 2009, Nagashio et al 2010, by applying advanced control theories in order to develop a baseline for future controller design technology for this class of satellite instead of existing classical PID control laws. This paper reports the on-orbit experiment results using them.…”

Section: Introductionmentioning

confidence: 99%

Design and Flight Test Results of Robust Attitude Controller for the ETS-VIII Spacecraft

Nagashio

Kida

Ohtani

et al. 2011

IFAC Proceedings Volumes

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This paper reports the flight test results of robust attitude controller for Engineering Test Satellite VIII (ETS-VIII) spacecraft. The main mission of ETS-VIII is to support nextgeneration mobile digital communications, and for this purpose it is equipped with two large deployable antenna reflectors and a pair of large solar paddles that rotate around the pitch axis. For the spacecraft, the authors have proposed and demonstrated several control methods based on the advanced control theories for the linear parameter varying multi-input multioutput system. The aim is to develop a baseline for future controller design technology for this class of satellite instead of existing classical PID control laws. This paper describes the on-orbit experiment results and compares these controllers performance.

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“…It is because modern spacecraft often employ large, deployed and light damping structures (such as solar paddles and antenna reflectors) to provide sufficient power supply and reduce launch costs [1][2][3][4][5][6]. During the control of the rigid body attitude, actuators play an important role of linking control commands to physical actions [7,8].…”

Section: Introductionmentioning

confidence: 99%

Robust fault-tolerant control for flexible spacecraft against partial actuator failures

Zhang

Qiao

et al. 2014

Nonlinear Dyn

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In this paper, we present a robust faulttolerant control scheme to achieve attitude control of flexible spacecraft with disturbances and actuator failures. It is shown that the control algorithms are not only attenuate exogenous bounded disturbances with attenuation level, but also able to tolerate partial loss of actuator effectiveness. The proposed controller design is simple and can guarantee the faulty closed-loop system to be quadratically stable with a prescribed upper bound of the cost function. The design algorithms are obtained by combining free weighting matrices method with linear matrix inequality technique. The effectiveness of the proposed design method is demonstrated in a spacecraft attitude control system subject to loss of actuator effectiveness.

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Design and implementation of robust symmetric attitude controller for ETS-VIII spacecraft

Cited by 51 publications

References 16 publications

Time-varying modal parameters identification of large flexible spacecraft using a recursive algorithm

Time-varying modal parameters identification of large flexible spacecraft using a recursive algorithm

Design and Flight Test Results of Robust Attitude Controller for the ETS-VIII Spacecraft

Robust fault-tolerant control for flexible spacecraft against partial actuator failures

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