TY - GEN
T1 - Identification of Spacecraft Attitude Control System Based on MOESP Subspace Method
AU - Yingjie, Pan
AU - Han, Gao
N1 - Publisher Copyright:
© The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2025.
PY - 2025
Y1 - 2025
N2 - This article investigates the identification of attitude system of spacecraft, with a particular focus on dealing with non-cooperative target spacecraft. During the interception of non-cooperative targets, their parameters may be unknown. Following the capture of a non-cooperative target by the service spacecraft, the primary objective is to maintain steadiness in the attitude control of the combined spacecraft. Establishing a state-space approach to model the system is essential for this purpose. Owing to the uncertainty in the parameters of the combined spacecraft's attitude control system, system identification methods are necessary to determine these parameters. Initially, this study develops a mathematical model of the spacecraft attitude control system. Subsequently, utilizing the subspace identification method based on the multivariable output-error state-space (MOESP) algorithm, a state-space model that accurately represents the original system is derived by comparing the system's input and output data. The model's validity is verified by comparing the output responses of the model and the actual system under different typical input signal excitations, demonstrating that the established model meets the identification criteria.
AB - This article investigates the identification of attitude system of spacecraft, with a particular focus on dealing with non-cooperative target spacecraft. During the interception of non-cooperative targets, their parameters may be unknown. Following the capture of a non-cooperative target by the service spacecraft, the primary objective is to maintain steadiness in the attitude control of the combined spacecraft. Establishing a state-space approach to model the system is essential for this purpose. Owing to the uncertainty in the parameters of the combined spacecraft's attitude control system, system identification methods are necessary to determine these parameters. Initially, this study develops a mathematical model of the spacecraft attitude control system. Subsequently, utilizing the subspace identification method based on the multivariable output-error state-space (MOESP) algorithm, a state-space model that accurately represents the original system is derived by comparing the system's input and output data. The model's validity is verified by comparing the output responses of the model and the actual system under different typical input signal excitations, demonstrating that the established model meets the identification criteria.
KW - Multivariable Output-error State Space (MOESP)
KW - Spacecraft Attitude Control System
KW - Subspace Identification
UR - http://www.scopus.com/inward/record.url?scp=105000363328&partnerID=8YFLogxK
U2 - 10.1007/978-981-96-2260-3_21
DO - 10.1007/978-981-96-2260-3_21
M3 - Conference contribution
AN - SCOPUS:105000363328
SN - 9789819622597
T3 - Lecture Notes in Electrical Engineering
SP - 212
EP - 220
BT - Advances in Guidance, Navigation and Control - Proceedings of 2024 International Conference on Guidance, Navigation and Control Volume 16
A2 - Yan, Liang
A2 - Duan, Haibin
A2 - Deng, Yimin
PB - Springer Science and Business Media Deutschland GmbH
T2 - International Conference on Guidance, Navigation and Control, ICGNC 2024
Y2 - 9 August 2024 through 11 August 2024
ER -