| High-Voltage DC (HVDC) aeronautical power system has the advantages such as low weight, easiness to realize redundancy, uninterruptible power supply and high power density, it has been attracting more and more attentions. It is very important to develop high efficiency, high power density and high reliability static inverter for the HVDC aeronautical power system.The thesis reviews the development status of the aeronautical power systems and aeronautical static inverters, and discusses the scheme for the three-phase static inverter, which is composed of three single-phase static inverters. Each single-phase static inverter adopts two-stage approach, a DC/DC stage followed by a DC/AC stage. The DC/DC stage converts 270VDC to 180VDC with isolation, and the DC/AC stage converts 180VDC to 115V/400Hz sinusoidal voltage.This thesis focuses on the development of the DC/DC stage, which adopted the phase-shifted zero-voltage-switching (ZVS) PWM full-bridge converter with two clamping diodes. The converter has the advantages including ZVS for the switches, no voltage spike across the rectifier diodes, simple circuit and constant frequency control. The operating principle of the converter is analyzed, and the design procedures of the main circuit and control circuit are presented.The loss of the converter is discussed including power devices, rectifier diode, magnetic components and etc., and the mathematic model of loss distribution and theoretical efficiency are obtained by means of MathCAD.The converter is analyzed by simulation, and a 1kW prototype converter is built in the lab, the simulation and experimental results verify the validity of the above analysis and design.
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