On-orbit system identification experiments on Engineering Test Satellite-VI

Adachi, Shuichi; Yamaguchi, Isao; Kida, Takashi; Sekiguchi, Takeshi; Yamada, Katsuhiko; Chida, Yuichi

doi:10.1016/s0967-0661(99)00032-5

Cited by 28 publications

(23 citation statements)

References 12 publications

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“…17 (2), 184-194 (2016) of appendages. (The detailed placement situations see the simulation examples in the subsequent section).…”

Section: Originals Of Illustrations Used In the Textmentioning

confidence: 99%

“…On-orbit identification experiments of spacecrafts that determine the modal parameters have been performed in some studies [1][2][3], such as the Galileo spacecraft and Hubble space telescope [4][5]. However, these identification experiments are mostly based on the linear time-invariant (LTI) system.…”

Section: Introductionmentioning

confidence: 99%

“…In existing identification algorithm for on-orbit spacecraft, the eigensystem realization algorithm (ERA) was mostly often used for the identification of modal parameters [1][2][3][4][5][9][10]. The ERA is a typical system realization method.…”

Section: Introductionmentioning

confidence: 99%

“…Then, the system modal parameters and state-space model matrices {A, B, C} are determined. However, the ERA was mainly based on the time-invariant and slow time-varying system [1][2][3][4]11]. For common timevarying system, the ERA is not always suitable.…”

Section: Introductionmentioning

confidence: 99%

“…Now we consider the situations for different system orders: the orders of system model are selected as 70, 110 and 150, Int'l J. of Aeronautical & Space Sci. 17 (2), 184-194 (2016) respectively. The average computation time for the recursive and pseudo modal method is shown in Table 3, where the relative computation efficiency (RCE) e RCE is defined as follows:…”

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confidence: 99%

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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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“…17 (2), 184-194 (2016) of appendages. (The detailed placement situations see the simulation examples in the subsequent section).…”

Section: Originals Of Illustrations Used In the Textmentioning

confidence: 99%