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Spacecraft structural system identification by modal testA structural parameter estimation procedure using the measured natural frequencies and kinetic energy distribution as observers is proposed. The theoretical derivation of the estimation procedure is described and its constraints and limitations are explained. This procedure is applied to a large complex spacecraft structural system to identify the inertia matrix using modal test results. The inertia matrix is chosen after the stiffness matrix has been updated by the static test results.
Document ID
19840048950
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chen, J.-C.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Peretti, L. F.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Garba, J. A.
(California Institute of Technology, Jet Propulsion Laboratory, Applied Mechanics Technology Section, Pasadena CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1984
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 84-1051
Accession Number
84A31737
Distribution Limits
Public
Copyright
Other

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