Problems on nonlinear dynamics of a control system for the spacecraft in their orientation initial modes are considered - during separation from a launcher rocket up to regular attitude stabilization in orbital reference frame. Developed methods, algorithms and the simulation results for the orientation initial modes of the small satellites and space robots are presented.
Nonlinear Dynamics of a Spacecraft Control System in the Orientation Initial Modes
01.06.2019
272701 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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