Active vibration suppression of a large flexible space structure is addressed. The system (experimental test bed), performance requirements, and system simulations and models are described. The structures is a 60-m truss beam attached to the Shuttle orbiter. A baseline control system is required to provide 5% structural damping for the first ten structural (flexible) modes of the truss beam. The control design approach used to achieve the damping is a decentralized velocity feedback type. Collocated actuator and sensor locations are given, with details of the model for the proof-mass actuating device, the linear DC motor.
Active vibration suppression for the mast flight system
Aktive Schwingungsunterdrueckung fuer ein grosses flexibles Raumfahrtsystem
Control Systems Magazine (IEEE) ; 9 , 1 ; 85-90
1989
6 Seiten, 4 Quellen
Article (Journal)
English