FIELD: mechanics; cosmonautics.
SUBSTANCE: invention refers to space vehicle (SV) orientation control. Method involves mathematical modelling of SV orbit, measurement of parametres of its angular movement, and determination, construction and maintenance of the specified SV orientation according to them. There also measured is kinetic momentum in powered gyro system (PGS). At that, according to the measured parametres of angular movement and PGS kinetic momentum there determined is law of variation of total disturbing moment acting on the space vehicle. There determined are nominal operating parameters of target load at standard SV orientation, as well as time intervals (Δti) at which parameters of SV angular movement are not measured. At the beginning of i interval there shifted is PGS kinetic momentum in the direction of SV axis oriented along vector of orbital angular speed. Considering the above law of variation of disturbing moment, and measured and specified parametres of angular movement and PGS kinetic momentum there predicted at i interval is the change of that kinetic momentum, which is required for maintaining the specified SV orientation. This variation is tried out by measuring the operating parametres of target load and by comparing them to the nominal ones. At mutual mismatch of these parametres there built is the specified SV orientation and then a new variation law of disturbing moment is determined. When this time does not go beyond i interval then PGS kinetic momentum is shifted as before, and when specifying the appropriate parametres SV orientation is controlled on the rest part of i interval. Otherwise, SV orientation is controlled as per measured parameters of its angular movement.
EFFECT: improving SV control reliability and increasing service life thereof due to maintaining standard SV orientation when data from instruments is not available.
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