| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 716064 | IFAC Proceedings Volumes | 2010 | 6 Pages |
Abstract
Problems on guidance and robust gyromoment attitude control of agile information satellite for remote sensing the Earth surface are considered. Elaborated methods for dynamic research of the spacecraft programmed angular motion at principle modes under external and parametric disturbances, partial discrete measurement of the state and digital control of the gyro moment cluster by the few-excessive gyrodine schemes, are presented.
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