Synthesis of a linearly interpolated gain scheduling controller for large flexible spacecraft ETS-VIII

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

doi:10.1016/j.conengprac.2011.02.005

Cited by 34 publications

(15 citation statements)

References 26 publications

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“…The non-linear behavior of the actuator is expressed as a poly topic multi model [9]. It is composed of several Linear Time Invari ant (LTI) models interpolated by barycentric coordinates to approximate non-linearities using continuous functions.…”

Section: Introductionmentioning

confidence: 99%

Multi-model observer and state feedback position control of a flexible robotic actuator

Huard

Grossard

Moreau

et al. 2012

IECON 2012 - 38th Annual Conference on IEEE Industrial Electronics Society

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This paper proposes a state feedback control of a lightweight electric actuator dedicated to manipulation tasks. Ta king advantage of an optimized back-drivable mechatronic de sign, the use of proprioceptive measures at the motor level enables the estimation of the unmeasured terminal position of the me chanical motor-to-joint transmission and force disturbance. An accurate model of the actuated mechanical flexible transmission is introduced to determine unmeasurable states with a model based observer. The observer and the controller are synthesized by tacking into account the non-linear dynamic behavior of the mechatronic system. Non-linearities are reformulated into a poly topic multi-model, and dynamic performances of the controlled system are fixed by root-clustering. This synthesis is performed through Linear Matrix Inequalities (LMIs) and is experimentally validated with a single degree-of-freedom manipulator.

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Section: Introductionmentioning

confidence: 99%

Multi-model observer and state feedback position control of a flexible robotic actuator

Huard

Grossard

Moreau

et al. 2012

IECON 2012 - 38th Annual Conference on IEEE Industrial Electronics Society

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“…It has been pointed out, however, that gain-scheduled controllers derived via solutions to LMIs for gain-scheduled synthesis may suffer from such complexity in implementation as requiring real-time computation of the coefficient matrices. Hamada et al [3] proposed gain-scheduled controllers with piecewise-affine functions in (approximated) LPV models and coefficient matrices of controllers, motivated by a necessity of reduction of computation of controllers implemented in spacecrafts. A spline-type solution of Manuscript received January 29, 2014; revised August 25, 2014; accepted July 26, 2015.…”

Section: Introductionmentioning

confidence: 99%

Gain‐Scheduled Control via Switching of LTI Controllers and State Reset

Masubuchi¹,

Ishii²,

Ohta³

et al. 2015

Asian Journal of Control

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This paper proposes a synthesis method of gain-scheduled control systems that switch linear time-invariant controllers according to hysteresis of the scheduling parameter. Stability and L 2 -gain analysis and synthesis methods for switched systems are applied to the switched gain-scheduled control synthesis using reset of the controller state, where also the reset law is computed via linear matrix inequalities (LMIs). In addition to optimization of an upper bound of L 2 -gain, we reduce jumps of control input via an auxiliary optimization. Numerical examples are presented to illustrate the switched gain-scheduled controller.

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“…It is a geosynchronous satellite at an altitude of approximately 35,786 km. 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].…”

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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Synthesis of a linearly interpolated gain scheduling controller for large flexible spacecraft ETS-VIII

Cited by 34 publications

References 26 publications

Multi-model observer and state feedback position control of a flexible robotic actuator

Multi-model observer and state feedback position control of a flexible robotic actuator

Gain‐Scheduled Control via Switching of LTI Controllers and State Reset

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

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