SYSTEM OF RETURN OF COURSE ORIENTATION OF SPACE VEHICLE USING ORBITAL GYROCOMPASS

摘要

FIELD: astronautics.;SUBSTANCE: system for the recovery of the course orientation (CO) of a spacecraft (SC) using an orbital gyrocompass (OGC) contains a device for orientation on the Earth (DOE), a unit of gyroscopic angular velocity meters (UAVM), navigation-ballistic unit (NBU), containing a central on-board computer (COBC) and satellite navigation equipment (SNE), nine adders, three amplification and conversion modules (ACM₁, ACM₂, ACM₃), cosine (CAT) and sine (SAT) angle transducers, four units of compensation for the influence of orientation channels (UCIC), three integrators, a module of logical zero (MLZ), a module for calculating the heading angle (MCHA), a module for forming a command (MFC), program rotation calculation module (PRCM), five normally closed keys (K_NC1÷K_NC5), five normally open keys (K_NO1÷K_NO5), stabilization system (SS).;EFFECT: quality is improved and the transition time is reduced when the spacecraft course orientation is restored with the use of free-form OGC.;1 cl, 3 dwg