FIELD: transport.
SUBSTANCE: method includes mathematical modelling of spacecraft (SC) orbit, measurement of powered gyroscopes angular momentum and - at certain flight intervals - SC angular motion parameters. These measurements help to support SC preset orientation and to determine disturbing moments impacting SC. At interval when SC angular motion parameters are not measured, powered gyroscopes angular momentum alterations required to support SC preset orientation are predicted. In conformity with prediction these gyroscopes are impacted and simultaneously target loading operation parameters are measured. From the moment of discrepancy of these parameters with their nominal rating in optimum SC orientation, again SC angular motion are measured, disturbing moments impacting SC are re-determined and SC orientation is reset. Then during remaining part of the said interval, as previously stated, again powered gyroscopes angular momentum alterations are predicted, and the set SC orientation is supported in conformity with prediction. If the said interval is exhausted, then control of SC orientation is performed as per measured parameters of its angular motion until next interval when SC angular motion parameters are not measured.
EFFECT: preservation of optimum spacecraft orientation in conditions of absence of information from devices measuring spacecraft angular motion.
10 dwg, 3 tbl
