NASA NTRS · 19920069461
CSI design of articulated space structures
Abstract
Integrated control and structural design of flexible spacecraft with articulated appendages is considered. A procedure is proposed by which the resulting design is optimal with respect to a measure of performance for all possible system articulation conditions. The controller design is of the dynamic dissipative type which provides guaranteed closed-loop stability. The procedure is demonstrated for a simple multibody flexible spacecraft model with an articulated appendage.
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Kelkar, Atul G., Koganti, Gopichand, Alberts, Thomas E., Hou, Gene, Woodard, Stanley E.. 1992-01-01. CSI design of articulated space structures. https://ntrs.nasa.gov/citations/19920069461
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