| With the increasing electrical applications in aircraft, the higher performances of aircraft power supply system are required. Besides enlarging the capacity of generator, secondary power system plays a more and more important role. Static inverters, with the advantage of high efficiency, high power density and high reliability, have been researched and developed in recent years. This paper involves two researches about aeronautical static inverter .In first part, the 400Hz/50Hz converter technology used in constant frequency AC power system is researched .A 7.5kVA aeronautical static inverter is designed and it transforms three-phase 115V/400Hz power supply system into 220V/50Hz single-phase power to meet some special equipments on aircraft. The inverter includes DC/DC converter and DC/AC inverter two-stage structures. The circuit topology, operation principle and parameter design of developed inverter is analyzed in this part. In second part, a 28V/270V bi-directional DC/DC converter for high voltage direct circuit is researched. A circuit which includes an isolated boost converter and a bridge converter is introduced and this topology is a current-fed and voltage-fed hybrid type. The principle of energy–flow bi-directionally is analyzed in detail. The control strategy of the converter is one side current regulated and the other side voltage regulated. The validity of the analysis is convinced by the simulation and experiment results.
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