KR102448970B1 - Electric power control apparatus and avionics equipment having the same - Google Patents

Abstract

The present invention provides an inrush current limiter for limiting the inrush current generated at the initial stage of power input; a power outage response unit that supplies power for a certain period of time when power is cut off; And it provides a power control device including a control unit for controlling the supply of power from the power outage response unit, and avionics equipment having the same.

Description

Power control apparatus and avionics equipment having the same

The present invention relates to a power control device, and more particularly, to a power control device for controlling an inrush current and maintaining power supply to a system such as an avionics device even when an input power is cut off.

Recently, multi-function and high-performance aircraft are required, and accordingly, the number of avionics (hereinafter, referred to as 'avionics equipment') mounted on the aircraft is increasing. In addition, since a large number of avionics are mounted in a predetermined space in an aircraft, they are closely installed in a very narrow space.

On the other hand, a power supply (Power Supply) is used to supply a necessary voltage in a system including the avionics equipment. However, in the initial stage when the power of the power supply device is supplied, an overshoot is instantaneously generated, and an inrush current is generated due to the overvoltage. This inrush current may cause a problem in the power supply, which may cause a malfunction in the downstream system. For example, internal components such as power lines, switches, rectifiers and capacitors can be damaged. In addition, it may interfere with other equipment using the same power source and cause a malfunction. Therefore, a conventional power supply is provided with a circuit for controlling the inrush current therein.

In order to suppress the inrush current, conventionally, two switches and a resistor are used. Since two switches are used, a separate device such as a signal processing unit or a control unit for controlling the on/off of the switches is required. Accordingly, since a separate device for controlling the switch is required, problems such as an increase in the unit price of a product, an increase in physical specifications, and a decrease in reliability may occur.

Also, there may be a case in which power is not input and power is cut off due to a malfunction of the power supply device or the like. In order to cope with such a power outage of the input power, a circuit and a control method for detecting the input power and changing the system were used in the prior art. To this end, a sensing unit for sensing input power and a separate control unit or signal processing unit for changing the system are required. Therefore, a separate device for system change is required, which may cause problems such as an increase in the unit price of the product, an increase in physical specifications, and a decrease in reliability.

Korean Patent No. 10-1538232 Korean Patent No. 10-1837205

The present invention provides a power control device capable of limiting an inrush current without a switch and a separate device for controlling the switch, and an avionics device having the same.

The present invention provides a power control device capable of responding to a power cut off of an input power without a separate device for detecting a power cut off of the input power, and an avionics device having the same.

The present invention provides a power control device capable of limiting an inrush current and simultaneously responding to a power cut of an input power source, and an avionics device having the same.

A power control apparatus according to an aspect of the present invention includes: an inrush current limiter for limiting the inrush current generated at the initial stage of power input; a power outage response unit that supplies power for a certain period of time when power is cut off; and a control unit for controlling the supply of power from the power outage response unit.

Further comprising a rectifying unit for converting AC power to DC power, the rectifier includes a plurality of bridge-coupled diodes.

The inrush current limiter includes a resistor.

The power outage response unit charges the input power and supplies the charged power when the power is cut off.

The disconnection counterpart includes a capacitor connected to the resistor to charge the input power through the resistor.

The disconnection counterpart further includes a diode provided at the front end of the resistor, and a first switch connected to the capacitor and connected in parallel to the resistor, wherein the first switch is controlled by switching by the controller.

The control unit includes a first switch driver for controlling the switching of the first switch, a second switch driver whose output level is adjusted according to input power, and an output of the first switch driver driven by the second switch driver and a second switch for adjusting the level.

The control unit includes a first voltage divider for controlling an output level of the second switch driver by distributing input power, and a second voltage divider for controlling an output level of the first switch driver by distributing an output of a first diode. include more

Avionics equipment according to another aspect of the present invention is a power supply for supplying power; an inrush current limiter for limiting the inrush current that is initially generated when the power is input; a power outage response unit charged by the power source and discharging the charged charges when the power source is cut off and supplying the power to the power source; a control unit for controlling the supply of power from the power outage response unit; a first load connected to the power supply; and a second load connected to the power supply unit and the power outage counterpart.

The second load receives power from the power supply unit and receives power from the power outage response unit when power is cut off.

The first load is configured as a system that allows a function stop when the power is cut off, and the second load is configured as a system that maintains a normal operation for a predetermined time when the power is cut off.

Avionics equipment according to another aspect of the present invention is a power supply for supplying power; an inrush current limiter for limiting the inrush current that is initially generated when the power is input; a power outage response unit for supplying charged charges to power when the power is cut off; a control unit for controlling the supply of power from the power outage response unit; a first load receiving power from the power supply unit and allowing a function stop when the input power is cut off; and a second load connected to the power supply unit and the power outage counterpart and maintaining a normal operation for a predetermined time when the power is cut off, wherein the power cut counterpart has a different charging path and a different discharge path.

The power cut counter part receives the power through the inrush current limiter and is charged, and supplies power to the second load without passing through the inrush current limiter during discharging.

The inrush current limiting unit includes a resistor, and the disconnection counterpart includes a capacitor connected to the resistor to charge the input power through a resistor, a diode provided at a front end of the resistor, and a second connected to the capacitor and connected in parallel with the resistor. a first switch, wherein the control unit is driven by a first switch driver for controlling the switching of the first switch, a second switch driver whose output level is adjusted according to input power, and the second switch driver to be driven by the second switch driver. and a second switch for controlling an output level of the first switch driver, wherein the capacitor is charged by power input through a diode and a resistor, and discharged through the first switch to supply power to a second load.

In the present invention, when power is inputted, power is charged to the capacitor of the power outage counterpart, and the inrush current is limited by using a resistor, and the power charged in the capacitor is supplied to the load when the input power is cut off. In addition, the present invention separates the system into a first load that can be cut off for a certain period of time and a second load that needs to maintain a normal operation, and supplies the power charged to the power outage response unit to the second load when the input power is cut off. That is, according to the present invention, the inrush current is limited by using an analog circuit, and a normal operation is possible for a predetermined time when the input power is cut off.

According to the present invention, the inrush current can be suppressed without a switch and a separate device for controlling the switch, and at the same time, it is possible to respond to the power outage of the input power without having a separate device for detecting the power cut off of the input power. . Accordingly, the present invention has the advantage of optimizing the physical specification by simplifying the power supply device, and reducing the weight/miniaturization of the power supply device. In addition, the reliability of the avionics equipment can be improved by dividing the system configuration of the avionics equipment into a first load and a second load so that power can be supplied to the first load for a predetermined time when the input power is cut off.

As a result, it is determined that the present invention will be a great improvement in the aviation field (Aerospace & Avionic, PAV, UAV, drone, etc.) requiring product reliability and weight reduction.

1 and 2 are block diagrams for explaining a power control apparatus and avionics equipment having the same according to an embodiment of the present invention.
3 is a circuit diagram of a power system of a power control device and an avionics device having the same according to an embodiment of the present invention.
4 and 5 are schematic diagrams for explaining a power control device and a method of driving an avionics device having the same according to an embodiment of the present invention.
6 and 7 are block diagrams for explaining a power control device and an avionics device having the same according to another embodiment of the present invention.
8 is a circuit diagram of a power system of a power control device and an avionics device having the same according to another embodiment of the present invention.
9 and 10 are schematic diagrams for explaining a power control device and a method of driving an avionics device having the same according to another embodiment of the present invention.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below, but will be implemented in a variety of different forms, and only these embodiments allow the disclosure of the present invention to be complete, and the scope of the invention to those of ordinary skill in the art It is provided for complete disclosure. In order to clearly express the various layers and each region in the drawing, the thickness was enlarged and the same reference numerals were used to refer to the same elements in the drawing.

1 and 2 are block diagrams for explaining a power control apparatus according to embodiments of the present invention, and are block diagrams for explaining a configuration of a power control apparatus according to input power and an avionics device having the same. That is, FIG. 1 is a block diagram of a power control device and avionics device receiving AC power, and FIG. 2 is a block diagram of a power control device and avionics device receiving DC power.

Referring to FIG. 1 , a power control apparatus receiving AC power according to an embodiment of the present invention may include a rectifying unit 100 , an inrush current limiting unit 200 , and a power outage response unit 300 . The rectifier 100 converts and supplies a power supply, for example, AC power supplied from an aircraft into a DC system inside the avionics equipment. In addition, the inrush current limiter 200 limits the inrush current generated when the avionics equipment is initially started. And, the power outage response unit 300 maintains the normal operation of the avionics equipment for a certain period of time even if the AC power supplied from the aircraft is temporarily cut off. That is, the power outage response unit 300 supplies power for a predetermined time when the AC power is cut off.

Referring to FIG. 2 , a power control apparatus receiving DC power according to another embodiment of the present invention may include an inrush current limiting unit 200 and a power outage response unit 300 . The inrush current limiter 200 limits the inrush current that occurs when the avionics equipment is initially started, and the power outage response unit 300 maintains the normal operation of the avionics equipment for a certain period of time even if the DC power supplied from the aircraft is temporarily cut off. let it do That is, the power control device receiving DC power does not include the rectifier 100 compared to the power control device receiving AC power, and the inrush current limiter 200 and the power failure response unit 300 perform the same function. .

On the other hand, the system receiving power through the power control device according to the embodiments of the present invention shown in FIGS. 1 and 2 , that is, the avionics equipment may be configured to include the first and second loads 410 and 420 . . At this time, according to the operation necessity of the avionics equipment, a system that maintains normal operation for a certain period of time when the input power is cut off is configured like the second load 420 , and a function stop allowing system is configured like the first load 410 . do. That is, the first load 410 is connected to the power supply or the rectifier 100 and receives DC power input by the power supply through the rectifier 100 or is directly supplied. In addition, the second load 410 is connected to the power supply or the rectifying unit 100 and at the same time connected to the power outage response unit 300 so that when power is input, the DC power input by the power supply is supplied through the rectifying unit 100 or The power is supplied directly, and power is supplied from the power outage response unit 300 when the power is temporarily cut off. Therefore, since the second load 420 is driven according to the output of the power outage response unit 200, it can be configured as a system that maintains a normal operation for a predetermined time when the input power is cut off, and the first load 410 is DC power or Since it is driven by DC power through the rectifier 100, it can be configured as a system that allows the function to stop for a certain period of time when power is cut off. Meanwhile, the loads including the first and second loads 410 and 420 may include various electronic devices that are driven by receiving power from the aircraft. For example, the load may include RF equipment, radar equipment, navigation equipment, and the like, and the first and second loads 410 and 420 may classify the equipment according to whether the normal operation is maintained when the input power is cut off.

Hereinafter, more specific embodiments of the power control device according to the present invention and the avionics equipment having the same will be described with reference to the drawings.

3 is a circuit diagram illustrating a power control device and an avionics device having the same according to an embodiment of the present invention.

Referring to FIG. 3 , the power control apparatus according to an embodiment of the present invention may include a rectifying unit 100 , an inrush current limiting unit 200 , and a power outage response unit 300 . In addition, the avionics device may include the power control device, first and second loads 410 and 420 , and first and second DC/DC converters 510 and 520 . The first DC/DC converter 510 may be connected to the first load 410 , and the second DC/DC converter 520 may be connected to the second load 420 .

The rectifier 100 may convert system power, for example, three-phase AC power input from an aircraft, into DC power to supply avionics equipment. The rectifying unit 100 may include a plurality of bridge-coupled diode devices 110 . In addition, the rectifier 100 may include a first capacitor C11 connected in parallel to the plurality of bridge-coupled diode elements 110 . That is, the rectifier 100 includes a plurality of bridge-coupled diode elements 110 connected between the first and second nodes Q11 and Q12, and the first and second nodes Q11 and Q12 connected between the bridge-coupled diodes. A first capacitor C11 connected in parallel with the plurality of diode devices 110 may be included. On the other hand, as shown in FIG. 2 , in the case of avionics equipment directly receiving DC power from an aircraft, the rectifying unit 100 is not provided because DC power is input.

The inrush current limiter 200 limits the inrush current generated when the avionics equipment is started. To this end, the inrush current limiting unit 200 allows the inrush current to flow through a different path instead of flowing to the first load 410 or the second load 420 to the first load 410 or the second load 420 . Limit inrush current. The inrush current limiter 200 may include a resistor R11 connected between the third node Q13 and the fourth node Q14. That is, the inrush current limiter 200 may limit the inrush current applied through the rectifier 100 through the first resistor R11 . The first resistor R11 controls the charge of the second capacitor C12 by controlling the movement of the current flowing into the second capacitor C12 of the disconnection counter 300, and thereby restricts the inrush current from flowing to the load. can That is, for example, when the first resistor R11 is not provided or when a diode is provided instead of the first resistor R11, the charging of the second capacitor C12 is faster than when the first resistor R11 is provided, and accordingly If an inrush current is generated accordingly, the movement to the load cannot be suppressed.

The power outage response unit 300 performs a function of allowing the avionics equipment to maintain normal operation for a certain period of time even if the input power supplied from the aircraft is temporarily cut off. To this end, the power outage response unit 300 may charge the power applied through the rectifier 100 , discharge the charged power, and supply it to the avionics equipment. The disconnection counter 300 includes a first diode D11 connected between the first node Q11 and the third node Q13 and a second diode D11 connected between the fourth node Q14 and the second node Q12. It may include a capacitor C12 and a second diode D12 connected between the fourth node Q14 and the third node Q13. That is, in the disconnection counterpart 300 , the first and second diodes D11 and D12 may be connected in the reverse direction. Also, the second capacitor C12 and the second diode D12 may be connected through different paths. That is, one terminal of the second capacitor C12, that is, the second node Q12 is connected to one terminal of the second DC/DC converter 520, and the output of the second diode D12, that is, the third node ( Q13) may be connected to the other terminal of the second DC/DC converter 520 . The power outage response unit 300 charges the second capacitor C12 when power is input, and transfers the charge charged in the second capacitor C12 when the input power is temporarily cut off to the second DC/DC converter 420 . may be supplied to the second load 420 through the

The first DC/DC converter 510 has an input terminal connected to the rectifier 100 and the first and second nodes Q11 and Q12 and an output terminal connected to the first load 410 . The second DC/DC converter 520 has an input terminal connected to the second and third nodes Q12 and Q13 and an output terminal connected to the second load 420 . That is, the first DC/DC converter 510 has an input terminal connected to the rectifying unit 100 , and the second DC/DC converter 520 has an input terminal connected to the rectifying unit 100 and the disconnection counterpart 300 . . At this time, according to the operation necessity of the avionics equipment, a system that maintains normal operation for a certain period of time when the input power is cut off is configured like the second load 420 , and a function stop allowing system is configured like the first load 410 . do. That is, since the second load 420 is driven by the output of the second DC/DC converter 420 according to the output of the power outage response unit 200, it can be configured as a system that maintains normal operation for a certain period of time when the input power is cut off. In addition, since the first load 410 is driven by the output of the first DC/DC converter 410 according to the output of the rectifier 100 , it may be configured as a system in which the function is allowed to stop for a certain period of time when the power is cut off. Therefore, it is possible to optimize the physical specifications of the avionics equipment, and to reduce the size and weight.

A method of driving the power control apparatus according to an embodiment of the present invention as described above will be described with reference to FIGS. 4 and 5 .

4, when the avionics equipment is initially started, AC power supplied from the aircraft is converted into DC power through the rectifier 100, and the DC power is a second capacitor ( C12) is charged. At the same time, the inrush current generated when power is input is limited through the resistor R11. That is, when power is applied, the inrush current is limited by the resistor R11 and charges the second capacitor C12. In addition, the DC power is supplied to the first load 410 through the first DC/DC converter 510 and is supplied to the second load 420 through the second DC/DC converter 520 . In the normal state, since the second capacitor C12 maintains a constant voltage and power for operating the avionics equipment is supplied through the first DC/DC converter 510, the power loss of the resistor R11 is very small.

Referring to FIG. 5 , when the input power is cut off, the internal DC system of the avionics equipment collapses, and the avionics equipment maintains its normal operation through the amount of power charged in the second capacitor C12 and the second diode D12. . That is, when the input power is cut off, the power charged in the second capacitor C12 is supplied to the second load 420 through the second diode D12. At this time, since the voltage charged in the second capacitor C12 is higher than the internal DC system of the avionics equipment, the first diode D11 is turned off, and the second diode D12 is turned on. . Therefore, it is possible to supply power to the avionics equipment for a predetermined time without power loss due to the resistor R11.

As described above, the power control apparatus according to an embodiment of the present invention may limit the inrush current generated when the system is normally started through the resistor R11. While limiting the inrush current through the resistor R11, the second capacitor C12 is charged to respond when the input power is cut off. In steady state, power is supplied to the load for system operation. However, when the input power is cut off, the first diode D11 is turned off and the second diode D12 is turned on so that the power charged in the capacitor C12 is supplied to the avionics equipment through the second diode D12 for a predetermined time. Normal operation can be maintained.

6 and 7 are block diagrams for explaining a power control device according to other embodiments of the present invention, and are block diagrams for explaining a configuration of an avionics device including a power control device according to input power. That is, FIG. 6 is a block diagram of a power control device and avionics device receiving AC power, and FIG. 7 is a block diagram of a power control device and avionics device receiving DC power.

Referring to FIG. 6 , the power control device receiving AC power according to an embodiment of the present invention may include a rectifying unit 100 , an inrush current limiting unit 200 , and a power outage response unit 300 . The rectifier 100 converts the AC power supplied from the power supply device, for example, the aircraft, into a DC system inside the avionics equipment and supplies it. In addition, the inrush current limiter 200 limits the inrush current generated when the avionics equipment is initially started. And, the power outage response unit 300 maintains the normal operation of the avionics equipment for a certain period of time even if the AC power supplied from the aircraft is temporarily cut off. In addition, another embodiment of the present invention may further include a control unit 600 for controlling the charging and discharging of the power outage response unit (300).

Referring to FIG. 7 , a power control device receiving DC power according to another embodiment of the present invention may include an inrush current limiter 200 and a power outage response unit 300 . That is, the power control device receiving DC power does not include the rectifier 100 as compared to the power control device receiving AC power, and the inrush current limiter 200 and the power failure response unit 300 perform the same function. . In addition, another embodiment of the present invention may further include a control unit 600 for controlling the charging and discharging of the power outage response unit (300).

On the other hand, the system receiving power through the power control device according to the embodiments of the present invention shown in FIGS. 1 and 2 , that is, the avionics equipment may be configured to include the first and second loads 410 and 420 . . At this time, according to the operation necessity of the avionics equipment, a system that maintains normal operation for a certain period of time when the input power is cut off is configured like the second load 420 , and a function stop allowing system is configured like the first load 410 . do. That is, since the second load 420 is driven according to the output of the power outage response unit 200, it can be configured as a system that maintains normal operation for a predetermined time when the input power is cut off, and the first load 410 is DC power or Since it is driven by DC power through the rectifier 100, it can be configured as a system that allows the function to stop for a certain period of time when power is cut off.

Hereinafter, more specific embodiments of a power control device and an avionics device having the same according to another embodiment of the present invention will be described with reference to the drawings.

8 is a circuit diagram of a power control device and an avionics device having the same according to another embodiment of the present invention.

Referring to FIG. 8 , a power control apparatus according to another embodiment of the present invention may include an inrush current limiter 200 and a power outage response unit 300 . In addition, although not shown, the rectifier may further include a rectifier for converting tubular power, for example, three-phase AC power input from the aircraft into DC power to supply the avionics equipment. That is, in another embodiment of the present invention, DC power may be converted and generated through the rectifying unit, or DC power may be applied without passing through the rectifying unit, as in the embodiment of the present invention. When a rectifier is included, the diode bridge described in the embodiment of the present invention of FIG. 3 may be provided. In addition, the power system of the avionics equipment may include the power control device, first and second loads 410 and 420 , and first and second DC/DC converters 510 and 520 . The first DC/DC converter 510 may be connected to the first load 410 , and the second DC/DC converter 520 may be connected to the second load 420 .

The inrush current limiter 200 limits the inrush current generated when the avionics equipment is started. To this end, the inrush current limiting unit 200 allows the inrush current to flow through a different path instead of flowing to the first load 410 or the second load 420 to the first load 410 or the second load 420 . Limit inrush current. The inrush current limiter 200 may include a resistor R11 connected between the second node Q12 and the third node Q13. That is, the inrush current limiter 200 limits the applied inrush current through the first resistor R11.

The power outage response unit 300 performs a function of maintaining the normal operation of the avionics equipment for a certain period of time even if the input power supplied from the aircraft is temporarily cut off. To this end, the power outage response unit 300 may charge the applied power and use it as an auxiliary power source. The disconnection counter 300 includes a first diode D11 connected between the first node Q11 and the second node Q12, and a resistor connected between the second node Q12 and the third node Q13. It may include a first switch S11 connected in parallel with R11, and a capacitor C12 connected between the third node Q13 and the ground terminal. Also, the power outage counter 300 may be connected to the second load 420 through the second DC/DC converter 520 . The power outage response unit 300 supplies the charge charged in the capacitor C12 to the second DC/DC converter 520 through the first switch S11 when the input power is temporarily cut off, and through this, the second load ( 420) can be supplied.

The first DC/DC converter 510 has an input terminal connected to the first node Q11 and an output terminal connected to the first load 410 . The first DC/DC converter 510 converts DC power into DC power used for the first load 410 . The second DC/DC converter 520 has an input terminal connected to the second node Q12 and an output terminal connected to the second load 420 . The second DC/DC converter 520 converts DC power into DC power used for the second load 420 . At this time, according to the operation necessity of the avionics equipment, a system that maintains normal operation for a certain period of time when the input power is cut off is configured like the second load 420 , and a function stop allowing system is configured like the first load 410 . do. That is, since the second load 420 is driven according to the output of the power outage response unit 200 , it can be configured as a system that maintains a normal operation for a predetermined time when the input power is cut off, and the first load 410 is the rectifier 100 ), it is driven by the output of the first DC/DC converter 410 according to the output, so it can be configured as a system that allows the function to stop for a certain period of time when power is cut off. Therefore, it is possible to optimize the physical specifications of the avionics equipment, and to reduce the size and weight.

The control unit 600 may be provided to control charging and discharging of the power outage response unit 300 . That is, the controller 600 may control the charging and discharging of the power outage responding unit 300 by switching the first switch S11 of the power outage responding unit 300 . The control unit 600 includes a first switch driver 610 for driving the first switch S11, a first voltage divider composed of the second and third resistors R12 and R13, and a distribution of the first voltage divider. A second switch driver 620 whose potential is adjusted according to a voltage, a second switch S12 driven by the second switch driver 620 to adjust the potential of the first switch driver 610, and the first switch A second voltage divider configured to adjust the potential of the driver 610 and composed of fourth and fifth resistors R14 and R15 may be included. In the control unit 600 , the level of the second switch driver 620 is determined according to the output of the second voltage divider, and the second switch S12 is driven according to the level of the second switch driver 620 . That is, when power is applied to the first voltage divider and the voltage is divided by the first voltage divider, the output of the second switch driver 620 maintains a predetermined potential or higher so that the second switch S12 may be turned on. Conversely, if no power is applied to the first voltage divider and thus the voltage is not divided to the first voltage divider, the output of the second switch driver 620 maintains a predetermined potential or less so that the second switch S12 may be turned off. have. Also, the level of the first switch driver 610 may be adjusted according to the turn-on or turn-off state of the second switch S12 . That is, when the second switch S12 is turned on, the level of the fifth node Q15 is lowered, and accordingly, the level of the first switch driver 610 is lowered, so that the first switch S11 is turned off, and the second switch ( When S12 is turned off, the level of the first switch driver 610 may increase to turn on the first switch S11 . In this way, the control unit 600 may drive the first switch S11 of the power outage responding unit 300 to control the charge charged in the power outage responding unit 300 to be supplied to the second load 420 .

A method of driving the power control apparatus according to another embodiment of the present invention as described above will be described with reference to FIGS. 9 and 10 .

Referring to FIG. 9 , when the avionics equipment is initially started, the internal system of the avionics equipment consists of a DC system, and the capacitor C12 for responding to a power failure is charged through the first diode D11. The inrush current generated at this time is limited through the resistor R11. At the same time, power for operating the avionics equipment is supplied to the first and second loads 410 and 420 through the first and second DC/DC converters 510 and 520 , respectively. In a normal state, the capacitor C12 maintains a constant voltage, and power for operating the avionics equipment is supplied to the first and second loads 410 and 420 through the first and second DC/DC converters 510 and 520 . Therefore, the power loss of the resistor R11 is very small. On the other hand, when DC power is supplied, a divided voltage is generated by the first voltage divider composed of the second and third resistors R12 and R13 of the control unit 600 and applied to the second switch driver 620 , and the second switch driver 620 maintains a level above a predetermined potential to turn on the second switch S12. Accordingly, the power supplied to the fifth node Q15 through the first diode D11 is bypassed to the ground terminal through the second switch S12. Accordingly, the fifth node Q15 maintains the level below the predetermined potential, and accordingly, the first switch driver 610 maintains the level below the predetermined potential to turn off the first switch S11 . Accordingly, while limiting the inrush current through only the resistor R11, the capacitor C12 may be charged with charge.

Referring to FIG. 10 , when the input power is cut off, the internal DC system of the avionics equipment is collapsed, and the avionics equipment maintains the normal operation through the amount of power charged in the capacitor C12 and the first switch S11 . That is, when the input power is cut off, the power charged in the second capacitor C12 is supplied to the second load 420 through the first switch S11 . At this time, due to the collapse of the DC power system of the avionics equipment, the second switch S12 due to voltage distribution of the second and third resistors R12 and R13 is turned off, and the voltage of the fourth and fifth resistors R14 and R15 is turned off. Through distribution, the first switch S11 is turned on. Therefore, it is possible to supply power to the avionics equipment for a certain period of time without power loss due to the resistor R11, and a high-efficiency power supply configuration without power loss (diode conduction voltage) occurring in the first diode D11 of an embodiment of the present invention. This is possible.

As described above, the power control apparatus according to another embodiment of the present invention may limit the inrush current generated when the system is normally started through the resistor R11. While limiting the inrush current through the resistor R11, the second capacitor C12 is charged to respond when the input power is cut off. In steady state, power is supplied to the load for system operation. However, when the input power is cut off, the second switch S12 is turned off and the first switch S11 is turned on so that the power charged in the capacitor C12 is supplied to the avionics equipment through the first switch S11 for a predetermined time. Normal operation can be maintained.

Although the technical idea of the present invention as described above has been described in detail according to the above embodiments, it should be noted that the above embodiments are for description and not for limitation. In addition, those skilled in the art will understand that various embodiments are possible within the scope of the technical spirit of the present invention.

100: rectifier 200: inrush current limiter
300: power outage response unit 400: load
500: DC/DC converter 600: control unit

Claims (15)

an inrush current limiter for limiting the inrush current generated at the initial stage of power input;
a power outage response unit that supplies power for a certain period of time when power is cut off; and
A control unit for controlling the supply of power from the power outage response unit,
The inrush current limiter includes a resistor,
The power outage response unit,
a diode provided in front of the resistor;
a capacitor connected to the resistor to charge the input power through the resistor;
and a first switch connected to the capacitor and connected in parallel to the resistor,
The first switch is a power control device that is switched by the control unit.
The power control device according to claim 1, further comprising a rectifier for converting AC power into DC power.
The power control device of claim 2 , wherein the rectifier includes a plurality of bridge-coupled diodes.
delete The power control device of claim 1 , wherein the power outage response unit charges the input power and supplies the charged power when the power is cut off.
delete delete The method according to claim 1, wherein the control unit,
a first switch driver for controlling the switching of the first switch;
a second switch driver whose output level is adjusted according to the input power;
and a second switch driven by the second switch driver to adjust an output level of the first switch driver. The method according to claim 8, wherein the control unit,
a first voltage divider configured to distribute input power to adjust an output level of the second switch driver;
The power control apparatus further comprising a second voltage divider for dividing the output of the first diode to adjust the output level of the first switch driver.
a power supply for supplying power;
an inrush current limiter for limiting the inrush current generated at the initial stage of power input;
a power outage response unit that is charged by the power source and discharges the charged charges when the power is cut off and supplies the power to the power source;
a control unit for controlling the supply of power from the power outage response unit;
a first load connected to the power supply; and
and a second load connected to the power supply unit and the power outage counter,
The first load is configured as a system that allows a function stop when power is cut off, and the second load is configured as a system that maintains normal operation for a predetermined time when power is cut off.
The avionics device of claim 10 , wherein the second load receives power from the power supply unit and receives power from the power outage countermeasure unit when power is cut off. delete a power supply for supplying power;
an inrush current limiter for limiting the inrush current generated at the initial stage of power input;
a power outage response unit for supplying the charged electric charge to the power source when the power is cut off;
a control unit for controlling the supply of power from the power outage response unit;
a first load receiving power from the power supply unit and allowing a function stop when the input power is cut off; and
and a second load connected to the power supply unit and the power outage response unit, and maintaining a normal operation for a predetermined time when power is cut off;
The disconnection counterpart has a different charging path and a different discharging path,
The inrush current limiter includes a resistor,
The disconnection counterpart includes a capacitor connected to the resistor to charge the input power through the resistor, a diode provided at the front end of the resistor, and a first switch connected to the capacitor and connected in parallel with the resistor,
The control unit includes a first switch driver for controlling the switching of the first switch, a second switch driver whose output level is adjusted according to input power, and an output level of the first switch driver driven by the second switch driver a second switch for controlling
The capacitor is charged by power input through a diode and a resistor, and is discharged through the first switch to supply power to a second load.
The avionics device of claim 13 , wherein the power outage response unit is charged by receiving power through the inrush current limiter, and supplies power to the second load without passing through the inrush current limiter during discharging. delete

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