Abstract
Some of the control problems and analysis of the construction dynamic properties of a discretely evolving space structure (DES) during the process of its in orbit assembly are considered. The equations of the DES attitude motion are deduced taking into account discrete change with time of the construction and its essential flexibility. The analysis of the changeable dynamic properties of the DES is presented. This control object is featured by variable parameters, high and variable number of freedom degrees and characteristics of a multi-frequency vibrating system. Sequence of the attitude control strategies that guarantee stable and high precision of the control throughout all stages of the assembly is suggested.
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