Methods for stellar-inertial navigation and gyromoment guidance of the agile land-survey satellites

The novel discrete algorithms for signal processing, calibration and alignment of a strapdown inertial navigation system for attitude determination of an agile spacecraft are presented. The problem on synthesis of the attitude guidance laws for an observation spacecraft at land surveying is considered. The spacecraft attitude guidance on selected sequence by interchanging its agile rotation maneuvers with the general boundary conditions and the scanning observation courses is performed by a gyro moment cluster. Numerical results demonstrating efficiency of the developed methods for the stellar-inertial navigation and synthesis of the gyromoment guidance laws at the area land survey are presented.