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Applied Physics and Mathematics

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FEATURES OF MATHEMATICAL DESCRIPTION OF THE ORIENTATION SYSTEM OF THE SATELLITE IN THE REGIME OF LARGE DEVIATIONS
V.S. RYABIKOV, N.N. SCHEGLOVA

Examines the control loop of spacecraft orientation in the orbital coordinate system using the principle of guided BIS. A comparative analysis of the kinematic equations for large angles of rotation of the spacecraft is carried out. The algebra of quaternions for transition from orbital to connected axes is applied. The formula of the skew-symmetric matrix of the relative rotation of the coupled axes and of the orbital axes coincides with the formula of the A.YU. Ishlinsky matrix obtained in a different way. The scheme of the closed system of stabilization of the spacecraft in large deviations is presented. Correction matrix recorded. The expressions of the angle corrections used to correct the accumulated calculation errors that arise due to the errors of angular velocity sensors, accumulated errors of integration of kinematic equations, as well as other computational and other errors are shown.
Key words: spacecraft, quaternions, orbital axis, related axis, the contour correction.


DOI: 10.25791/pfim.06.2018.333

Contacts: E-mail: SheglovaNN@yandex.ru

Pp. 50-55.

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