On One Class of Systems for Controlling the Orientation of Artificial Earth Satellites
Combination systems of control are used for orienting satellites designed for protracted flight times. The best control for satellites travelling in relatively low orbits is provided by control systems in which the load on a flywheel is imposed by a magnetic torquer. Investigation of such systems (1, 2, 3, 7) has explained the most characteristic properties of practical application of such systems, their design, and their construction.
Many problems of design and computation of combination systems with magnetic drives for the case of three-dimensional orientation of satellites, however, require further investigation. The greatest difficulties in such investigations are due to the difficulty of combining the processes of controlling angular motion and loading of flywheels in a general dynamic pattern. Another important problem is synthesis of flywheel systems characterized by control-channel crosstalk.
Minimum mean-square error in satellite orientation;
Minimum energy consumption for torquing flywheels.
The same assumptions as adopted in (3) lie at the base of the investigation.
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