Journal
IEEE TRANSACTIONS ON INDUSTRIAL ELECTRONICS
Volume 66, Issue 11, Pages 8648-8658Publisher
IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC
DOI: 10.1109/TIE.2018.2884172
Keywords
Flexible spacecraft; observers; partial differential equations (PDEs); vibration control; well-posedness
Categories
Funding
- National Natural Science Foundation of China [61203060]
- Science and Technology Planning Project of Guangdong Province of China [2017B090910006, 2016B090927010, 2016B010126001]
- Opening Foundation of Key Research and Development Program of Guangdong province
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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.
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