A mathematical model for a general multibody flexible spacecraft is obtained. The generic spacecraft considered consists of a flexible central body to which a number of flexible multibody structures are attached. The coordinate systems used in the derivation allow effective decoupling of the translational motion of the entire spacecraft from its rotational motion about its center of mass. The derivation assumes that the deformations in the bodies are only due to elastic motions. The dynamic model derived is a closed-form vector-matrix differential equation. The model developed can be used for analysis and simulation of many realistic spacecraft configurations.
Mathematical modeling of a class of multibody flexible spacecraft structures
01.12.1994
Report
Keine Angabe
Englisch
Dynamic modeling of flexible multibody structures
IEEE | 1999
|PAPERS - Dynamic Modeling of Flexible Multibody Structures
Online Contents | 1999
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