KR101766668B1 - Current buffer battery control system for satellite power system and method thereof - Google Patents

Current buffer battery control system for satellite power system and method thereof Download PDF

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Publication number
KR101766668B1
KR101766668B1 KR1020150188411A KR20150188411A KR101766668B1 KR 101766668 B1 KR101766668 B1 KR 101766668B1 KR 1020150188411 A KR1020150188411 A KR 1020150188411A KR 20150188411 A KR20150188411 A KR 20150188411A KR 101766668 B1 KR101766668 B1 KR 101766668B1
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KR
South Korea
Prior art keywords
battery
power
power supply
loads
load
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KR1020150188411A
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Korean (ko)
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KR20170078161A (en
Inventor
이상록
전문진
임성빈
최석원
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한국항공우주연구원
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    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J1/00—Circuit arrangements for dc mains or dc distribution networks
    • H02J1/10—Parallel operation of dc sources
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
    • G01R31/36—Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/13—Receivers
    • G01S19/34—Power consumption
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
    • H02J7/0036—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits using connection detecting circuits
    • H02J7/0054—
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery

Abstract

A current buffer battery control system and method for a satellite power supply of the present invention includes a power supply (10) for supplying power to a plurality of loads (20), a power supply (10) (40) connected in series between the power supply device (10) and the load (20) and distributing the power required by the load (20) A battery 30 for current buffer connected in parallel between the power distributing device 40 and the plurality of loads 20 and a plurality of loads 30 connected in parallel with the battery 30, And a control unit 1000 connecting or disconnecting the battery 30 according to an amount of power required by the load 20. The life of the battery is extended by controlling the connection of the battery according to the required power and the charged amount of the battery , Can reduce the weight of the satellite It has an effect.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a current buffer battery control system for a satellite power supply,

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a current buffer battery control system for a satellite power supply apparatus and a control method thereof, and more particularly, to a control system and a control method for efficiently controlling a current buffer battery used in a power supply apparatus of a satellite.

The design of a power system applied to a satellite depends on the power consumption of the device in which it is installed. When a device in which a power system is configured to consume power is called a load, it is designed in consideration of the power consumption of the load and the power supply amount of the power supply. There is a situation where the power consumption of the load is greater than the power supply of the power supply depending on the system. To overcome this situation, a battery is connected in parallel to the load and the power supply, In other words, a system that assists the supply of power to a battery connected in parallel when a power shortage occurs is called a current buffer system.

The lifetime of the battery used in the current buffer system is determined by various factors. Typical examples thereof are a charge-discharge depth (DoD) and a charge-discharge current. The charge / discharge depth indicates how much of the charged current is used and then the battery is recharged when the battery is fully charged at 100%. FIG. 1 is a graph showing the number of charge / discharge cycles and the capacity reduction of a battery according to three charge / discharge depths (100%, 50%, and 30%). As shown in FIG. The lower the depth, the greater the number of times charge and discharge can be done and the longer the use is shown.

Another factor affecting battery life and capacity is the battery charge and charge / discharge current ratio. FIG. 1B is a graph showing the number of charging / discharging times and the capacity reduction of the battery according to the C rate (the ratio of the battery capacity to the charging / discharging current, the higher the charging / discharging current is). The lower the charging / discharging current is, It is possible to charge / discharge of the recovery and shows that it can be used for a long time.

No. 1363697 ("Power Supply Protection Device", registration date 2014.02.10.), Which relates to a conventional power supply protection device, is connected between a diode and a load, which is forward-connected to the output terminal of a constant voltage source, A power supply protection device including a switching device for switching power supply to the load is proposed and a protection device for stably maintaining the power supplied to the load is proposed.

However, in the current buffer system used in the conventional artificial power source device as shown in FIG. 2, the battery 3 is continuously connected to the power source 1 and the load 2 to repeatedly charge and discharge, And the capacity was decreased. Particularly, due to the characteristics of a satellite which is difficult to repair when it is on a track, the decrease in the life and capacity of the battery is a fatal factor, and it has a problem that affects the life of the satellite originally planned.

Korean Registered Patent No. 1363697 ("Power Supply Protective Device ", registered on Feb. 10, 2014).

It is an object of the present invention to provide a current buffer battery control system for a satellite power supply which can increase the service life of a battery by controlling charge and discharge of the current buffer battery have.

The present invention also provides a battery control system capable of reducing the weight of a satellite by allowing a current buffer battery for a satellite power supply device to use a battery having a smaller capacity than a conventional one.

According to an aspect of the present invention, there is provided a current buffer battery control system for a satellite power supply, including: A power supply 10 connected to the load 20 at all times and a power supply 10 connected in series between the power supply 10 and a plurality of loads 20 for distributing the power required by the load 20 A power distribution device (40) is connected in series to the power distribution device (40) and is connected in parallel between the power supply (10) and the load (20) A battery 30 for current buffer connected to or disconnected from the battery 30 and a plurality of loads 20 connected in parallel between the power distribution device 40 and a plurality of loads 20, (20) to the amount of electric power required And a controller (1000) for determining whether the power supply (10) and the load (20) are connected to the battery (30).

The control unit 1000 includes a load operation state monitoring unit 100 connected in parallel between the power distribution unit 40 and the load 20 to monitor the power required by the load 20, A battery charge sensing unit 200 connected to the battery 30 to measure a charge amount of the battery 30 and a battery charge sensing unit 200 connected in series between the battery 30 and the power distribution unit 40, A switch 300 for determining whether the power distribution device 40 is connected or not and a switch 300 for receiving signals from the load operation state monitoring unit 100 and the battery charge sensing unit 200, And a switch control unit 400 for determining the opening and closing of the battery 30 and regulating the charging amount and the charging power of the battery 30. [

The switch control unit 400 closes the switch 300 when the power required by the loads 20 is higher than the power that the power supply unit 10 can supply, To the plurality of loads (20).

The switch control unit 400 may be configured such that the power required by the plurality of loads 20 is lower than the power that the power supply unit 10 can supply and the charge amount of the battery 30 is lower than a predetermined reference The switch 300 is closed and the battery 30 is connected to the power supply device 10 to charge the battery 30.

When the power required by the load 20 is lower than the power that the power supply device 10 can supply and the charge amount of the battery 30 is higher than a predetermined reference, And disconnects the battery (30) from the power supply (10) and the load (20) by opening the switch (300).

In addition, the current buffer battery control system for a satellite power supply apparatus of the present invention further includes a charge / discharge measuring unit 500 connected to the battery 30 to measure the number of times of charge / discharge.

In addition, the power distribution device 40 controls the charging current of the battery 30 according to the degree of increase / decrease in the number of times the battery 30 is charged / discharged.

The current buffer battery control method for a satellite power supply device according to the present invention includes the steps of monitoring power required for the loads 20 through the load operation monitoring unit 100, When the power required by the plurality of loads 20 is higher than the power that can be supplied by the power supply device 10, the switch 300 is closed The battery 30 is connected to the plurality of loads 20 and the power required by the plurality of loads 20 is lower than the power that the power supply device 10 can supply, The switch 300 is closed and the battery 30 is connected to the power supply unit 10 to charge the battery 30 when the charge amount of the battery 30 is lower than a predetermined reference, If the required power is When the amount of charge of the battery 30 is lower than a power that the source supply device 10 can supply and the charge amount of the battery 30 is higher than a predetermined reference, the switch 300 is opened to connect the battery 30, the power supply device 10, And a switch control step of disconnecting the load (20) of the load (20).

According to the present invention as described above, unnecessary charging and discharging are prevented in the current buffer battery control system for a satellite power supply device, thereby extending the service life of the battery.

In addition, according to the present invention, the current buffer battery for a satellite power supply device can use a battery having a small capacity compared to the conventional one, thereby reducing the weight of the satellite. In the conventional case, the lifetime reduction due to the constant charge / discharge caused by the battery being always connected when the size of the battery is determined. However, according to the present invention, when the battery is not used, the battery is electrically isolated It is possible to increase the lifetime of the battery, and thus to select a battery having a capacity as small as the lifetime increase.

1 is a graph showing the lifetime of a battery according to the charging / discharging depth and charging current of the battery
2 is a schematic diagram of a current buffer battery control system for a conventional satellite power supply;
3 is a block diagram of a first operation example of a current buffer battery control system for a satellite power supply apparatus according to the present invention
4 is a block diagram of a second operation example of a current buffer battery control system for a satellite power supply apparatus according to the present invention
5 is a block diagram of a third operation example of a current buffer battery control system for a satellite power supply apparatus according to the present invention
6 is a flowchart for explaining a current buffer battery control method for a satellite power supply apparatus according to the present invention.

Hereinafter, a current buffer battery control system for a satellite power supply apparatus according to the present invention will be described in detail with reference to the accompanying drawings. First, the role of the configuration of the current buffer battery control system for a satellite power supply device according to the present invention will be briefly described, and an operation example that varies according to the amount of power required by the power source and the load will be described. Will be described.

3 is a schematic view of a current buffer battery control system for a satellite power supply apparatus according to the present invention and a first operation example.

3, the current buffer battery control system for a satellite power supply of the present invention includes a power supply 10 for supplying power required for a plurality of loads 20, a power supply 10 for supplying power to a plurality of loads 20, A power distributing device 40 connected in series between the power distributing device 40 and the power distributing device 40 for distributing the power required by the load 20, A current buffer battery 30 connected between the power distributing device 40 and the load 20 in parallel and connected in parallel between the power distributing device 40 and a plurality of loads 20, And a controller (1000) for connecting or disconnecting the battery (30) according to the amount of power required by a plurality of the loads (20).

The power supply 10 is a device for supplying power required for a plurality of loads 20.

The power distributing device 40 is a device that is connected in series between the power supply device 10 and a plurality of loads 20 to distribute the necessary power to the load 20 or the battery 30. The power distribution device 40 used in the aerospace field, especially satellite, is usually designed to overcome the insufficient power supply channel of the power supply and has only power distribution and transient interruption functions without regulating function. Therefore, the noise due to the operation of the variable load 20a and the constant load 20b affects the power supply device 10, thereby deteriorating the power supply characteristic. When the battery 30 to be described later is connected to the power distribution device 40, the noise is reduced.

A plurality of loads 20 are devices that require power for use in a satellite, such as a drivetrain, a cooling device, a sensor, or other devices required in the aerospace field. In the embodiment of the present invention shown in Fig. 3, the load 20 is divided into a fluctuating load 20a and a constant load 20b, each of which has a large fluctuation amount depending on the degree of fluctuation. For example, the driving of a compressor required for a cooling device used in a satellite is a representative example of a variable load requiring a large amount of electric power in a short period of time. A sensor and a control unit for monitoring and controlling various devices of a satellite are representative examples of loads at all times. Particularly, in the case of a compressor of a chiller driving apparatus, particularly, a large amount of electric power is required for operation, and electric noise is generated by the rotation of the compressor. Therefore, by connecting a battery for a current buffer, power replenishment and noise elimination are effected .

The battery 30 is connected in parallel between the power supply unit 10 and the load 20 in series with the power supply unit 40 so that the power supply unit 10 can supply power And supplies power to the load (20) when the total sum of the power required by the load (20) is large.

The load operating state monitoring unit 100 is connected in parallel between the power distributing apparatus 40 and the load 20 to monitor the power required by the load 20. [ The load operation state monitoring unit 100 monitors the power required by the load 20 and compares the power with the power that the power supply unit 10 can supply.

The battery charge sensing unit 200 is connected to the battery 30 to measure a charge amount of the battery 30. [ Since the battery 30 is connected to the power supply unit 10 and the load 20, when the amount of charge of the battery 30 is low, the power supply unit 10 charges the battery 30, As a result, the charge amount is increased. The charge amount of the battery 30 measured by the battery charge sensing unit 200 measures how much electric power is charged to the battery 30 in comparison with the maximum chargeable amount and has a percentage value. As described in the Background of the Invention, the maximum chargeable amount varies depending on the number of charge / discharge cycles and the charge / discharge depth of the battery, and therefore, it is a value that decreases as it is used. There may be a situation where the amount of charge of the battery 30 is continuously connected to the load 20 and the power is continuously supplied and the amount of charge is depleted to supply power to the load 20. However, The capacity of the battery 30 is determined in consideration of the amount of power consumed and the amount of power supplied to the power supply unit 10 and the power supply unit 20. Also, since it is temporary that the load 20 consumes more power than the power supply 10 can supply, the capacity of the battery 30 is determined by a line that is not exhausted.

The switch 300 is connected in series between the battery 30 and the power distributing device 40 to determine whether the battery 30 is connected to the power distributing device 40 or not. The expression that the switch 300 is used in a general electric device or an electric circuit means that the switch 300 is electrically connected to both sides of the switch to turn on the switch 300, The expression "open" means to turn OFF the electrical connection between the components connected to both sides. When the switch 300 is closed, the battery 30 is connected to the power distribution device 40, and power is supplied to the load 20 through the power distribution device 40.

The switch control unit 400 receives a signal from the load operation state monitoring unit 100 and the battery charge sensing unit 200 and determines the opening and closing of the switch 300 according to the signal, Adjust the charge amount and charge power.

In addition, the current buffer battery control system for a satellite power supply apparatus of the present invention further includes a charge / discharge measuring unit 500 connected to the battery 30 for measuring the number of times of charge and discharge, The charging current of the battery 30 can be adjusted according to the degree of increase in the number of times of recovery. As described above, by adjusting the charge current according to the number of charging / discharging times, the charging efficiency of the battery can be increased and the service life can be extended.

The load operation state monitoring unit 100 measures the power required by the load 20 and transmits the measured power to the switch control unit 400. The battery charge sensing unit 200 also checks the state of charge of the battery 30 and transmits the charge state to the switch control unit 400. The switch control unit 400 compares the information received from the load operation state monitoring unit 100 and the battery charge sensing unit 200 with the power that the power supply unit 10 can supply and closes the switch 300 Whether to open or not.

Hereinafter, operation examples varying depending on the states of the power supply device 10, the load 20, and the battery 30 will be described, respectively.

[First operation example]

Figure 3 illustrates a first operating embodiment of a current buffer battery control system for a satellite power supply of the present invention in which the power required by the load 20 is supplied by the power supply 10 Power and the amount of charge of the battery 30 is higher than a predetermined reference.

The switch control unit 400 activates the switch 300 to connect the battery 30 to the load 20 so that the battery 30 is supposed to assist the power supply unit 10 do. 3 is an electric power supplied from the power supply device 10, A2 is electric power supplied from the battery 30, and A3 is the electric power supplied to the load 20 by the combination of A1 and A2 Power.

[Second and Third Working Examples]

FIG. 4 illustrates a second operational embodiment of a current buffer battery control system for a satellite power supply of the present invention, in which the power required by the load 20 is supplied by the power supply 10 Power and the amount of charge of the battery 30 is lower than a predetermined reference.

In the above state, the power supply device 10 sufficiently supplies power to the load 20. Since the battery 30 needs to be charged to a predetermined reference or more, the battery 30 and the power supply unit 10 are connected to each other to charge the battery 30. 4 shows that the power A1 supplied from the power supply unit 10 is divided into the power A2 supplied to the battery 30 and the power A3 supplied to the load 20, A2 and the power A3. In the second operation example, when the battery 30 is connected to the power supply device 10 to charge the battery 30 and the charged amount of the battery 30 becomes equal to or greater than a predetermined reference value, (300) to prevent the battery (30) from being charged. The charging amount of the battery 30 is greater than the reference charging amount and the switch control unit 400 opens the switch 300 as in the third operation example, which is shown in FIG.

FIG. 6 is a flowchart illustrating a method of controlling a current buffer battery control system for a satellite power supply according to the present invention.

The current buffer battery control method for a satellite power supply apparatus according to the present invention firstly monitors the power required for the loads 20 through the load operation monitoring unit 100, The charging amount of the battery 30 is detected.

In the first operation example according to the detection value, when the power required by the plurality of loads 20 is higher than the power that the power supply device 10 can supply, the switch control unit 400 switches the switch 300) to connect the battery (30) to the plurality of loads (20).

In the second operation example, the switch control unit 400 determines that the power required by the plurality of loads 20 is lower than the power that the power supply unit 10 can supply, The switch 300 is closed and the battery 30 is connected to the power supply unit 10 to charge the battery 30 when the voltage is lower than a predetermined reference.

In the third operation example, the switch control unit 400 determines that the power required by the load 20 is lower than the power that the power supply unit 10 can supply, The switch 300 is opened to disconnect the battery 30 from the power supply unit 10 and the load 20. [

It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the scope of the present invention as defined by the appended claims.

10: Power supply
20: Load
20a: Variable load
20b: Always load
30: Battery
40: Power distribution device
100: Load operation state monitoring unit
200: battery charge detection unit
300: Switch
400: Switch control section
500: charge / discharge measuring unit
1000:
A1: Power supplied from the power source
A2: Battery power
A3: Power supplied to the load

Claims (6)

A current buffer battery control system for a satellite power supply,
A power supply (10) always connected to the load (20) to supply the necessary power to the plurality of loads (20);
A power distribution device (40) connected in series between the power supply (10) and the plurality of loads (20) and distributing power required by the load (20);
The power supply system according to any one of the preceding claims, wherein the power supply device (10) and the load (20) are connected in series to the power supply device (40) A battery 30 for current buffer; And
And a plurality of loads 20 connected in parallel between the power distributing device 40 and the plurality of loads 20 and connected in series with the battery 30 to supply power to the power supply device And a controller (1000) for determining whether or not the load (20) and the battery (30) are connected to each other.
The apparatus of claim 1, wherein the controller (1000)
A load operation state monitoring unit 100 connected in parallel between the power distributing apparatus 40 and the load 20 to monitor the power required by the load 20,
A battery charge sensing unit 200 connected to the battery 30 to measure a charged amount of the battery 30,
A switch 300 connected in series between the battery 30 and the power distributing device 40 for determining whether the battery 30 is connected to the power distributing device 40,
Receives a signal from the load operation state monitoring unit 100 and the battery charge sensing unit 200 and determines the opening and closing of the switch 300 according to the signal to adjust the charge amount and the charge power of the battery 30 A switch control unit 400;
And the current buffer battery control system for a satellite power supply.
3. The apparatus of claim 2, wherein the switch controller (400)
When the power required by the plurality of loads 20 is higher than the power that can be supplied by the power supply apparatus 10, the switch 300 is closed and the battery 30 is connected to the plurality of loads 20 Current buffer battery control system for a satellite power supply.
3. The apparatus of claim 2, wherein the switch controller (400)
When the power required by the plurality of loads 20 is lower than the power that the power supply device 10 can supply and the amount of charge of the battery 30 is lower than a predetermined reference, the switch 300 is closed And the battery (30) is charged by connecting the battery (30) to the power supply device (10).
3. The apparatus of claim 2, wherein the switch controller (400)
When the power required by the plurality of loads 20 is lower than the power that can be supplied by the power supply apparatus 10 and the charged amount of the battery 30 is higher than a predetermined reference, And disconnects the battery (30) from the power supply (10) and the plurality of loads (20).
A method of controlling a current buffer battery using a current buffer battery control system for a satellite power supply according to claim 2,
Monitoring power required for the plurality of loads (20) through the load operation state monitoring unit (100);
Sensing a charged amount of the battery (30) through the battery charge sensing unit (200);
When the power required by the plurality of loads 20 is higher than the power that can be supplied by the power supply apparatus 10, the switch 300 is closed and the battery 30 is connected to the plurality of loads 20 Connect,
When the power required by the plurality of loads 20 is lower than the power that the power supply device 10 can supply and the amount of charge of the battery 30 is lower than a predetermined reference, the switch 300 is closed The battery 30 is connected to the power supply unit 10 to charge the battery 30,
When the power required by the plurality of loads 20 is lower than the power that can be supplied by the power supply apparatus 10 and the charged amount of the battery 30 is higher than a predetermined reference, And a switch control step of disconnecting the battery (30) from the power supply (10) and the plurality of loads (20).
KR1020150188411A 2015-12-29 2015-12-29 Current buffer battery control system for satellite power system and method thereof KR101766668B1 (en)

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KR101766668B1 true KR101766668B1 (en) 2017-08-09

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