Design features of the spacecraft vehicle onboard equipment of the command-measuring system to control it in the zone of its coverage from a ground station and outside it

Principle of design and initial data for design of a command-measuring system (CMS), intended to control the low-orbit spacecraft (SC) and SC, designed to operate on the geostationary orbit at the stage of their output to the state security service are considered. With two control loops, as contained in CMS - between the ground station of CMS and SC and between the CMS, satellite-relay and SC, allows providing control of SC throughout its orbit flight. The problem questions of creation of CMS onboard equipment and ways of their solution are discussed.