Patent ID: 7859874
Filing Date: 2010-12-28
Classification: H02M,Y02B

Abstract:
1. An aircraft device power supply adapted to be connected to either an aircraft alternating current (AC) power bus or to an aircraft direct current (DC) power bus, and comprising: a first subcircuit having an input and an output, the first subcircuit configured to accept an AC power signal, convert the AC power signal to a lower voltage, and output a rectified AC power signal, when the power supply is connected to an aircraft AC power bus; an AC/DC switchover subcircuit having a first input connected to the output of the first subcircuit and a second input, and further having a switchover output, the AC/DC switchover subcircuit configured to: a power factor correction subcircuit having an input connected to the switchover output, and further having an output, the power factor correction subcircuit configured to correct a power factor of a rectified AC power signal, when the power supply is connected to the aircraft AC power bus, and further configured to output a DC power signal having a first voltage; and a DC-DC step-down converter having an input connected to the output of the power factor correction subcircuit, and further having a system voltage output, the DC-DC step-down converter configured to reduce the first voltage to a second voltage lower than said first voltage.