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An optimization-based integrated controls-structures design methodology for flexible space structuresAn approach for an optimization-based integrated controls-structures design is presented for a class of flexible spacecraft that require fine attitude pointing and vibration suppression. The integrated design problem is posed in the form of simultaneous optimization of both structural and control design variables. The approach is demonstrated by application to the integrated design of a generic space platform and to a model of a ground-based flexible structure. The numerical results obtained indicate that the integrated design approach can yield spacecraft designs that have substantially superior performance over a conventional design wherein the structural and control designs are performed sequentially. For example, a 40-percent reduction in the pointing error is observed along with a slight reduction in mass, or an almost twofold increase in the controlled performance is indicated with more than a 5-percent reduction in the overall mass of the spacecraft (a reduction of hundreds of kilograms).
Document ID
19930007426
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Maghami, Peiman G. (NASA Langley Research Center Hampton, VA, United States)
Joshi, Suresh M. (NASA Langley Research Center Hampton, VA, United States)
Armstrong, Ernest S. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1993
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-TP-3283
NAS 1.60:3283
L-17080
Accession Number
93N16615
Funding Number(s)
PROJECT: RTOP 590-14-51-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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