A MODULAR POWER CONTROL UNIT DESIGN FOR HIGH POWER SATELLITES FROM 8KW TO 25KW

摘要

A trend in recent years has been a steady increase of the payload power of telecommunication spacecraft (SC). To reduce the burden of the thermal control and to utilise more efficiently the power sources, solar arrays and batteries, higher bus voltages have been introduced. This paper presents an overall modular power control unit (PCU) design as well as a detailed module design of the power conversion modules for a 100V regulated bus application in a power range of 8kW up to about 25kW. The PCU topology regarding mainbus (MB) controlling is based on a two domain main error amplifier (MEA) using the ESA patented [1] sequential switching & serial shunt regulator (S4R) and battery discharge regulators (BDRs) for power conversion. PCU packaging, thermal and mechanical interfaces PCU→SC as well as the electrical interfaces to the SC will be discussed. Special emphasis is put on the two power conversion modules, S4R shunt regulator module and the BDR module.