SYSTEM FOR CONTROLLING SPATIAL ORIENTATION OF SPACECRAFT USING GIMBALLESS ORBITAL GYROCOMPASS

摘要

FIELD: aviation.;SUBSTANCE: invention relates to aviation and space instrument making and can be used in systems for control of angular position of spacecrafts (SC), in which orientation system using strap down orbital gyrocompasses (SOGC) are used. For this purpose, in output circuits of local vertical plotter (LVP) by roll and pitch adders are included, one per each channel so that their inputs are connected to corresponding outputs of LVP, orientation control module (OCM), first and second inputs of the OCM by roll and pitch are connected to outputs of corresponding adders at LVP output, and roll and pitch outputs of OCM are connected to inputs of first and eighth adders respectively, output circuits of first, second and third integrators include first module of direct conversion process angles of spacecraft stabilization, first, second and third inputs of which are connected to outputs of first, second and third integrators respectively. At that, control system allows to perform SC program turns relative to orbital coordinate system (OCS) simultaneously over heading, roll and pitch while SOGC continues to operate normally, without any disturbance of orbital gyrocompassing mode.;EFFECT: technical result is expansion of functional capabilities.;1 cl, 9 dwg