Universal AC or DC Aircraft Device Power Supply Having Power Factor Correction
First Claim
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;
output the rectified AC power signal, when the power supply is connected to the aircraft AC power bus and not to an aircraft DC power bus; and
output a DC signal, when the power supply is connected to the aircraft DC power bus and not to the aircraft AC power bus;
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.
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Accused Products
Abstract
An aircraft device power supply is capable of connecting to either an AC or a DC power bus provided on an aircraft. When connected to an aircraft'"'"'s AC power bus, an AC power signal is EMI-filtered, stepped down in voltage to the same voltage as that of the DC power bus, and then rectified. When connected to an aircraft'"'"'s DC power bus, a DC power signal is EMI-filtered before it is merged with the rectified AC power signal via an AC/DC switchover subcircuit. The output of the AC/DC switchover subcircuit is input to a power factor correction subcircuit which outputs a boosted DC voltage, regardless of which of the AC or DC aircraft power buses is connected to the power supply. A step down converter reduces the boosted DC voltage to a lower, system voltage which may then be further reduced or modified, as appropriate for device to be powered.
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Citations
23 Claims
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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:
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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; output the rectified AC power signal, when the power supply is connected to the aircraft AC power bus and not to an aircraft DC power bus; and output a DC signal, when the power supply is connected to the aircraft DC power bus and not to the aircraft AC power bus; 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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. An aircraft-mountable device adapted to be connected to either an aircraft alternating current (AC) power bus or to an aircraft direct current (DC) power bus, the aircraft-mountable device having a power supply comprising:
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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; output the rectified AC power signal, when the power supply is connected to the aircraft AC power bus and not to an aircraft DC power bus; and output a DC signal, when the power supply is connected to the aircraft DC power bus and not to the aircraft AC power bus; 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. - View Dependent Claims (13)
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14. 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:
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an AC electromagnetic interference (EMI) filter having a first input connectable to an aircraft AC power bus and a first output, the AC EMI filter configured to output a filtered AC power signal, when the power supply is connected to the aircraft AC power bus; a DC EMI filter having a second input connectable to an aircraft DC power bus and a second output, the DC EMI filter configured to output a filtered DC power signal, when the power supply is connected to the aircraft DC power bus; a first subcircuit having an input connected to the first output of the AC EMI filter and a third output, the first subcircuit configured to accept the filtered AC power signal, convert the filtered AC power signal to a lower voltage, and output a rectified AC power signal, when the power supply is connected to the aircraft AC power bus; an AC/DC switchover subcircuit having inputs connected to the second and third outputs, and further having a switchover output, the AC/DC switchover subcircuit configured to; output the rectified AC power signal, when the power supply is connected to the aircraft AC power bus and not to the aircraft DC power bus; and output the filtered DC power signal, when the power supply is connected to the aircraft DC power bus and not to the aircraft AC power bus; a power factor correction subcircuit having an input connected to the switchover output, and further having a fourth 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 fourth output, 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. - View Dependent Claims (15, 16, 17, 18, 19, 20, 21, 22, 23)
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Specification