Control microelectronic systems for power conditioning of advanced spacecraft

There are considered the major problems of the control unit organization for spacecraft power conditioning system. It is offered a problem solution of intellectual control unit organization based on special purposed system on a chip. The architecture, software and hardware of the microprocessor unit for a digital control circuit implementation are presented. The ground test results of voltage buck regulator are shown. It is shown that the minimal finite duration of transients process in case step change of load current in power module is achievable.