Boundary output feedback control of a flexible spacecraft system with input constraint. Issue 5 (18th January 2018)

• Record Type: Journal Article
• Authors: Fu, Yun; Liu, Yu; Huang, Daoping
• Is Part Of: IET control theory & applications. Volume 12:Issue 5(2018)
• Page Start: 571
• Page End: 581
• Publication Date: 2018-01-18
• Subjects: state feedback -- vibration control -- aerospace control -- vehicle dynamics -- observers -- partial differential equations; boundary state output feedback control -- flexible spacecraft system -- vibration control -- input saturation constraint -- spacecraft dynamics -- flexible appendages -- rigid body -- coupled partial differential equations -- ordinary differential equations -- control law -- high‐gain observer -- disturbance observers -- system performance -- boundary disturbances -- spacecraft system stability; Control theory -- Periodicals; Automatic control -- Periodicals; 629.8312
• DOI: 10.1049/iet-cta.2017.0567
• Languages: English
• ISSNs: 1751-8644

Abstract

Abstract : This study is concerned with vibration control of a flexible spacecraft system in the presence of disturbances and input saturation constraint. The dynamics of the spacecraft consisting of a rigid body and two flexible appendages is presented by the coupled partial differential equations and ordinary differential equations. The first boundary state feedback control is adopted when the spacecraft system states can be measured. The second boundary output feedback control is employed when there exists the unmeasurable state in the proposed control law. A high‐gain observer is developed to estimate the unmeasurable system state, two auxiliary systems are designed to prevent the presence of input saturation from destroying the system performance and two disturbance observers are established to handle the unknown boundary disturbances. The well‐posedness and stability of the spacecraft system are proved. Simulation results are presented to demonstrate the effectiveness of the proposed control schemes.