Modeling and Observer-Based Vibration Control of a Flexible Spacecraft With External Disturbances

• Published in: IEEE transactions on industrial electronics (1982) Vol. 66; no. 11; pp. 8648 - 8658
• Main Authors: Liu, Yu, Fu, Yun, He, Wei, Hui, Qing
• Format: Journal Article
• Language: English
• Published: New York IEEE 01.11.2019; The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
• Subjects: Attitude control; Boundary control; Computer simulation; Control systems; Control systems design; Control theory; Decentralized control; Disturbance observers; Dynamic models; Flexible spacecraft; Mathematical model; observers; Ordinary differential equations; Partial differential equations; partial differential equations (PDEs); Space vehicles; Spacecraft tracking; Vibration control; Vibrations; Well posed problems; well-posedness
• ISSN: 0278-0046; 1557-9948
• DOI: 10.1109/TIE.2018.2884172

This paper outlines the vibration reduction of a spacecraft with flexible appendage subject to external disturbances. The hybrid dynamic model of the spacecraft is described by both partial differential equations and ordinary differential equations. A vibration control scheme consisting of two boundary control laws and a distributed control law is developed to restrain the spacecraft's vibration and track the desired attitude. An infinite-dimensional disturbance observer is introduced as a feedforward compensator to handle unknown external disturbances. Based on the semigroup theory, the extended LaSalle's invariance principle and Lyapunov analysis, the well-posedness and stabilities of the designed control system are both discussed. Simulation results are given for validating the effectiveness of the developed vibration control scheme.