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Evaluation of on-line pulse control for vibration suppression in flexible spacecraftA numerical simulation was performed, by means of a large-scale finite element code capable of handling large deformations and/or nonlinear behavior, to investigate the suitability of the nonlinear pulse-control algorithm to suppress the vibrations induced in the Spacecraft Control Laboratory Experiment (SCOLE) components under realistic maneuvers. Among the topics investigated were the effects of various control parameters on the efficiency and robustness of the vibration control algorithm. Advanced nonlinear control techniques were applied to an idealized model of some of the SCOLE components to develop an efficient algorithm to determine the optimal locations of point actuators, considering the hardware on the SCOLE project as distributed in nature. The control was obtained from a quadratic optimization criterion, given in terms of the state variables of the distributed system. An experimental investigation was performed on a model flexible structure resembling the essential features of the SCOLE components, and electrodynamic and electrohydraulic actuators were used to investigate the applicability of the control algorithm with such devices in addition to mass-ejection pulse generators using compressed air.
Document ID
19870015080
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Masri, Sami F. (University of Southern California Los Angeles, CA, United States)
Date Acquired
September 5, 2013
Publication Date
July 13, 1987
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NAS 1.26:180391
USC-53-4507-0031
NASA-CR-180391
Accession Number
87N24513
Funding Number(s)
CONTRACT_GRANT: NAG1-636
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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