DocumentCode :
3084813
Title :
Experimental demonstration of active vibration control for flexible structures
Author :
Phillips, David J. ; Hyland, D. ; Collins, E.G.
Author_Institution :
Harris Corp., Melbourne, FL
fYear :
1990
fDate :
5-7 Dec 1990
Firstpage :
2024
Abstract :
Active vibration control of flexible structures for future space missions is addressed. Three experiments that successfully demonstrate control of flexible structures are described. The first is a pendulum experiment. The structure is a 5 m compound pendulum and was designed as an end-to-end test bed for a linear proof mass actuator and its supporting electronics. Experimental results are shown for a maximum-entropy/optimal-projection controller designed to achieve 5% damping in the first two pendulum modes. The second experiment was based upon the Harris Multi-Hex prototype experiment apparatus. This is a large optical reflector structure comprising a seven-panel array and supporting truss which typifies a number of generic characteristics of large space systems. The third experiment involved control design and implementation for the ACES structure at NASA Marshall Space Flight Center. The authors conclude with some remarks on the lessons learned from conducting these experiments
Keywords :
aerospace test facilities; distributed parameter systems; large-scale systems; vibration control; 5 m; ACES structure; Harris Multi-Hex prototype experiment; active vibration control; compound pendulum; flexible structures; linear proof mass actuator; optical reflector structure; pendulum experiment; seven-panel array; space missions; Control design; Damping; Electronic equipment testing; Flexible structures; Hydraulic actuators; Optical arrays; Optimal control; Prototypes; Space missions; Vibration control;
fLanguage :
English
Publisher :
ieee
Conference_Titel :
Decision and Control, 1990., Proceedings of the 29th IEEE Conference on
Conference_Location :
Honolulu, HI
Type :
conf
DOI :
10.1109/CDC.1990.203979
Filename :
203979
Link To Document :
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