Spacecraft Attitude Control: A Nonlinear Robust Control Approach
博士 === 國立成功大學 === 電機工程學系碩博士班 === 90 === In this dissertation, nonlinear control , mixed and LMI control design methods are proposed to solve large-angle robust attitude control and tracking of spacecraft. The robust attitude control problem is formulated as thruster control and wheels control wher...
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ndltd-TW-090NCKU54421832018-06-25T06:05:29Z http://ndltd.ncl.edu.tw/handle/m8wwcm Spacecraft Attitude Control: A Nonlinear Robust Control Approach 非線性強健控制設計方法於人造衛星姿態控制之研究 Long-Life Show 壽鶴年 博士 國立成功大學 電機工程學系碩博士班 90 In this dissertation, nonlinear control , mixed and LMI control design methods are proposed to solve large-angle robust attitude control and tracking of spacecraft. The robust attitude control problem is formulated as thruster control and wheels control where the desired stability and disturbance rejection are achieved. For the ROCSAT-3 spacecraft, a highly accurate and robust attitude control is desired during the orbit-raising phase and the other mission modes. The three-axis attitude control is achieved using 1) four body-fixed, canted thrusters or 2) a cluster 4 wheels. The nonlinear dynamic equations of the satellite are derived and the control requirements are stated. The dissertation investigates both attitude stabilization and tracking problems. As to the former, the nonlinear controller parameters are designed using nonlinear control , mixed and linear matrix inequality (LMI) method in thruster and wheels control models. As to the latter, the nonlinear controller that asymptotically tracks a desired reference trajectory under parameter variations and external disturbance is investigated. Asymptotic tracking is ensured under suitable restraints of the reference inputs. Simulation results based on the ROCSAT-3 system are then presented to demonstrate the proposed design method. Jyh-Ching Juang 莊智清 2002 學位論文 ; thesis 137 en_US |
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博士 === 國立成功大學 === 電機工程學系碩博士班 === 90 === In this dissertation, nonlinear control , mixed and LMI control design methods are proposed to solve large-angle robust attitude control and tracking of spacecraft. The robust attitude control problem is formulated as thruster control and wheels control where the desired stability and disturbance rejection are achieved. For the ROCSAT-3 spacecraft, a highly accurate and robust attitude control is desired during the orbit-raising phase and the other mission modes. The three-axis attitude control is achieved using 1) four body-fixed, canted thrusters or 2) a cluster 4 wheels. The nonlinear dynamic equations of the satellite are derived and the control requirements are stated. The dissertation investigates both attitude stabilization and tracking problems. As to the former, the nonlinear controller parameters are designed using nonlinear control , mixed and linear matrix inequality (LMI) method in thruster and wheels control models. As to the latter, the nonlinear controller that asymptotically tracks a desired reference trajectory under parameter variations and external disturbance is investigated. Asymptotic tracking is ensured under suitable restraints of the reference inputs. Simulation results based on the ROCSAT-3 system are then presented to demonstrate the proposed design method.
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author2 |
Jyh-Ching Juang |
author_facet |
Jyh-Ching Juang Long-Life Show 壽鶴年 |
author |
Long-Life Show 壽鶴年 |
spellingShingle |
Long-Life Show 壽鶴年 Spacecraft Attitude Control: A Nonlinear Robust Control Approach |
author_sort |
Long-Life Show |
title |
Spacecraft Attitude Control: A Nonlinear Robust Control Approach |
title_short |
Spacecraft Attitude Control: A Nonlinear Robust Control Approach |
title_full |
Spacecraft Attitude Control: A Nonlinear Robust Control Approach |
title_fullStr |
Spacecraft Attitude Control: A Nonlinear Robust Control Approach |
title_full_unstemmed |
Spacecraft Attitude Control: A Nonlinear Robust Control Approach |
title_sort |
spacecraft attitude control: a nonlinear robust control approach |
publishDate |
2002 |
url |
http://ndltd.ncl.edu.tw/handle/m8wwcm |
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