Abstract
AbstractProblems of nonlinear modelling, dynamic analysis and simulation of spatial motion by a spacecraft with a flexible weak damping structure, are considered. The obtained results on a multi-rate filtering measurements and a pulse-width control of the jet engines' thrust, simulation of attitude motion for the communication satellite with large-scale solar array panels at modes of initial damping, guidance on the Sun and on the Earth, are presented. Attitude motion of a flexible spacecraft at pulse-width control and spin-up rotors of six single-gimbal control moment gyros (gyrodines), is considered. Results on analysis of the spacecraft nutation and flexible oscillations, and also guidelines according to a logic in sequence of the gyrodine's rotors spin-up, are represented.
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