WO2022019517A1 - Système et procédé de commande de la puissance d'une pile à combustible - Google Patents

Système et procédé de commande de la puissance d'une pile à combustible Download PDF

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Publication number
WO2022019517A1
WO2022019517A1 PCT/KR2021/008344 KR2021008344W WO2022019517A1 WO 2022019517 A1 WO2022019517 A1 WO 2022019517A1 KR 2021008344 W KR2021008344 W KR 2021008344W WO 2022019517 A1 WO2022019517 A1 WO 2022019517A1
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Prior art keywords
fuel cell
power
drone
control system
load
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PCT/KR2021/008344
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English (en)
Korean (ko)
Inventor
황춘환
정용식
김영득
김준승
권형준
Original Assignee
(주)두산 모빌리티 이노베이션
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Publication of WO2022019517A1 publication Critical patent/WO2022019517A1/fr

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    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L58/00—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles
    • B60L58/30—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
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    • B64U50/34—In-flight charging
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L3/00—Electric devices on electrically-propelled vehicles for safety purposes; Monitoring operating variables, e.g. speed, deceleration or energy consumption
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L3/00—Electric devices on electrically-propelled vehicles for safety purposes; Monitoring operating variables, e.g. speed, deceleration or energy consumption
    • B60L3/0023—Detecting, eliminating, remedying or compensating for drive train abnormalities, e.g. failures within the drive train
    • B60L3/0053—Detecting, eliminating, remedying or compensating for drive train abnormalities, e.g. failures within the drive train relating to fuel cells
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L53/00—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles
    • B60L53/20—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles characterised by converters located in the vehicle
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B60L58/00—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles
    • B60L58/40—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for controlling a combination of batteries and fuel cells
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    • H—ELECTRICITY
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    • H01M8/04537—Electric variables
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    • H01M8/04313—Processes for controlling fuel cells or fuel cell systems characterised by the detection or assessment of variables; characterised by the detection or assessment of failure or abnormal function
    • H01M8/04537—Electric variables
    • H01M8/04544—Voltage
    • H01M8/04559—Voltage of fuel cell stacks
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
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    • H01M8/04694—Processes for controlling fuel cells or fuel cell systems characterised by variables to be controlled
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    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
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    • H02J3/38—Arrangements for parallely feeding a single network by two or more generators, converters or transformers
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    • H—ELECTRICITY
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    • H02J2207/20—Charging or discharging characterised by the power electronics converter
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Definitions

  • the present invention relates to a power control system and method for a fuel cell, and more particularly, to a power control system and method for a fuel cell that improves the operating efficiency of power supplied to a load such as a drone.
  • Drone is a generic term for an unmanned aerial vehicle without a human on board. Drones, largely controlled by radio waves, were initially used militarily to practice intercepting air planes, anti-aircraft artillery or missiles.
  • attack drones there is a form in which a plurality of propellers are arranged in a radial direction like a multicopter and maneuver in a free direction.
  • wing-type or multi-copter-type drones are being used for purposes such as reconnaissance or bomb dropping.
  • drones are expanding. Small drones have been developed and are being used for leisure, and the popularity of drones is gradually expanding to the extent that drone pilot competitions are held.
  • delivery industry is planning and implementing a delivery mechanism that transports ordered products using drones.
  • the present invention has been devised to solve the problems of the related art as described above, and an object of the present invention is to provide a power control system and method for a fuel cell that improves the operating efficiency of power supplied to a load such as a drone. is in
  • the present invention for achieving the above objects relates to a power control system of a fuel cell, the fuel cell generating power and including a cathode terminal and an anode terminal at an output terminal; a control module for controlling power supply between the fuel cell and a load consuming power; a high output mode disposed in the control module and configured to supply high output power from the fuel cell to the load; and a low output mode disposed in the control module and configured to supply relatively low low output power compared to the high output mode from the fuel cell to the load.
  • the fuel cell and the load may be directly connected in a circuit.
  • a converter unit for converting an output between the fuel cell and the load in the low output mode, converts the high voltage generated in the fuel cell into a low voltage and supplies it to the load.
  • a battery disposed in the control module and supplying power to the load in parallel with the fuel cell may further include.
  • a state detector connected to the fuel cell and configured to detect a state of the fuel cell, wherein the state detector includes at least a current value, a voltage value, a temperature value, and a pressure of the fuel cell value can be detected.
  • the state detection unit includes: a current sensor for measuring the current state of the fuel cell; a voltage sensor for measuring a voltage state of the fuel cell; a temperature sensor measuring the current temperature of the fuel cell and measuring whether the fuel cell operates within an appropriate temperature range; and a pressure sensor that measures the pressure applied to the fuel cell.
  • control module may further include a short-circuit unit disposed to be connected between the cathode terminal and the anode terminal of the fuel cell and disposed.
  • the short circuit unit includes: a short circuit switch connected between the cathode terminal and the anode terminal of the fuel cell; and a short circuit resistor connected between the short circuit switch and the cathode terminal, and provided to prevent deterioration due to a reverse potential phenomenon occurring in the fuel cell according to a short circuit between the cathode terminal and the anode terminal.
  • the short circuit unit when the actual measured power value of the fuel cell measured and calculated by the current sensor and the voltage sensor of the state detection unit is smaller than a preset power Ref value, the short circuit unit is activated and the cathode terminal and the The anode terminal can be shorted.
  • a current pulse is applied to the fuel cell to remove oxides on the surface of the fuel cell, and a hydration region may be formed in the fuel cell.
  • a plurality of fuel cells may be disposed, and a plurality of short-circuit portions may be respectively connected to cathode terminals and anode terminals formed in the plurality of fuel cells.
  • the plurality of short circuit units may not operate at the same time.
  • the smallest actual measured power among the plurality of short circuits connected to the plurality of fuel cells It can operate sequentially from any one short circuit connected to any one fuel cell whose value is calculated.
  • a plurality of the fuel cells are provided, the cathode terminals of the plurality of fuel cells are respectively connected to a plurality of switches, and whether the plurality of fuel cells are operated is individually determined by the plurality of switches. can be controlled with
  • the converter unit may include a plurality of converters respectively connected to the cathode terminals of the plurality of fuel cells.
  • some of the plurality of converters become upper converters, and some of the plurality of converters become lower converters, and the upper converter and the upper converter may be connected to each other by a converter connection line.
  • the converter unit may be a single converter that is integrally connected to the cathode terminals of the plurality of fuel cells, respectively.
  • the load may be a drone
  • the low power mode may operate during takeoff, landing or initial startup of the drone
  • the high power mode may operate during flight of the drone.
  • power when a voltage drop occurs due to an overload in the fuel cell during flight of the drone supplying power to the drone in the high output mode, power may be supplied in parallel through the battery.
  • the converter unit converts the power of the fuel cell to the battery can be charged.
  • the present invention relates to a power control method of a fuel cell, comprising: a fuel cell including a cathode terminal and an anode terminal at an output terminal; a control module for controlling power supply between the fuel cell and a load consuming power; a high output mode arranged in a circuit and directly connecting the fuel cell and the load in a circuit, and a low output power relatively low compared to the high output mode by converting the high voltage of the fuel cell to a low voltage through a converter unit disposed in the control module It may be a power control method of a fuel cell using a power control system of a fuel cell including a low output mode for supplying power to a load, and a battery disposed in the control module and supplying power to the load in parallel with the fuel cell.
  • the load is a drone
  • the low power mode may operate during takeoff and landing of the drone, initial start-up or standby state
  • the high power mode may operate during flight of the drone.
  • power when a voltage drop occurs due to an overload in the fuel cell during flight of the drone supplying power to the drone in the high output mode, power may be supplied in parallel through the battery.
  • the converter unit converts the voltage of the fuel cell by performing the low output mode to charge the battery can do.
  • the power control system of the fuel cell is disposed in the control module and further includes a short circuit part disposed to be connected between the cathode terminal and the anode terminal of the fuel cell, and the actual measured power of the fuel cell When the value is smaller than the preset power Ref value, the short circuit unit is activated to short-circuit the cathode terminal and the anode terminal.
  • the power control system of the fuel cell includes the plurality of fuel cells, and a plurality of short circuits are connected to each of the cathode and anode terminals formed in the plurality of fuel cells, and the plurality of The short circuits may be configured to not act simultaneously.
  • the smallest actual measured power among the plurality of short circuits connected to the plurality of fuel cells It may be configured to sequentially operate from any one short circuit connected to any one fuel cell whose value is calculated.
  • power is supplied from the fuel cell in a low output mode during takeoff, landing or initial start-up of the drone, and power is supplied from the fuel cell in a high output mode during flight of the drone.
  • power is supplied in parallel through the battery.
  • the low output mode is performed so that the converter unit converts the power of the fuel cell to charge the battery.
  • the current and voltage of the fuel cell are measured in real time even during flight of the drone to determine the power generation state of the fuel cell, and according to the state, the cathode terminal and the anode terminal of the fuel cell are short-circuited to supply current to the fuel cell.
  • FIG. 1 is a view showing a power control system of a fuel cell according to the present invention.
  • FIG. 2 is a view showing the power flow in a high output mode and a low output mode in the power control system of the fuel cell according to the present invention.
  • FIG. 3 is a graph showing the relationship between power operation and drone operation of the fuel cell power control system according to the present invention.
  • FIG. 4 is a diagram illustrating power supply through the battery together with a high output mode of the fuel cell when a voltage drop occurs due to an overload in the fuel cell in the power control system of the fuel cell according to the present invention
  • FIG. 5 is a diagram illustrating a power flow for charging a battery by converting power of a fuel cell in a converter in the power control system for a fuel cell according to the present invention
  • FIG. 6 is a view showing another form of a converter in the power control system of the fuel cell according to the present invention disclosed in FIG. 1 .
  • FIG. 7 is a view showing another form of a converter unit in the power control system of the fuel cell according to the present invention disclosed in FIG. 1 .
  • FIG. 1 is a view showing a power control system for a fuel cell according to the present invention.
  • the power control system of the fuel cell includes a fuel cell 10 , a control module P, a state detection unit 100 , a short circuit unit 40 , a high output mode (F1), and a low output mode (F2). , the battery 80 and the converter unit 30 may be included.
  • the fuel cell 10 is configured by stacking a plurality of stacks, and generates electric power by an electrochemical reaction of hydrogen and oxygen in each stack, and an output terminal may include a cathode terminal (+) and an anode terminal (-). .
  • the fuel cell is connected to an input terminal of a main board. Therefore, the cathode terminal (+) and the anode terminal (-), which are components included in the output terminal of the fuel cell, may be connected to the input terminal of the main board in the system.
  • the control module P may control power supply between the fuel cell 10 and the load 90 that consumes power.
  • the control module P may be a controller board that an operator can control using software.
  • the load 90 may be various power consuming devices, in particular, may be a drone.
  • the control structure to be described below in the present invention is basically considered to be compact and lightweight so that it can be applied to a drone.
  • the state detection unit 100 may be connected to the fuel cell 10 and detect the state of the fuel cell 10 .
  • the state detection unit 100 may perform a function of detecting at least a current value, a voltage value, a temperature value, and a pressure value of the fuel cell 10 .
  • the state detection unit 100 may be configured to include a current sensor, a voltage sensor, a temperature sensor, and a pressure sensor.
  • the current sensor measures the current state of the fuel cell 10
  • the voltage sensor measures the voltage state of the fuel cell 10
  • the temperature sensor measures the current temperature of the fuel cell 10 , Whether the fuel cell 10 operates within an appropriate temperature range is measured, and the pressure sensor measures the pressure applied to the fuel cell 10 .
  • the current sensor may measure a current value of the fuel cell 10
  • the voltage sensor may measure a voltage value of the fuel cell 10 .
  • an I-V curve expressing the relationship between current and voltage as a graph is applied, and the actual power value of the fuel cell 10 is calculated based on the values measured by the current sensor and the voltage sensor.
  • the current sensor and the voltage sensor are disposed inside the control module (P), are circuitly connected to the fuel cell (10), and are transferred from the fuel cell (10) to the load (90).
  • the power value can be measured.
  • the short circuit part 40 may be disposed in the control module P, and may be disposed to be connected between the cathode terminal and the anode terminal of the fuel cell 10 .
  • the short circuit part may include a short circuit switch and a short circuit resistor.
  • the short-circuit switch may be connected between a cathode terminal and an anode terminal of the fuel cell 10 , and the short-circuit resistor may be connected between the short-circuit switch and the cathode terminal.
  • the short circuit unit 40 may be a Field Effect Transistor (FET).
  • FET Field Effect Transistor
  • the field effect transistor FET
  • FET field effect transistor
  • a plurality of the fuel cells 10 may be connected to the control module P.
  • a plurality of short circuit portions may be respectively connected to the cathode terminal and the anode terminal formed in the plurality of fuel cells.
  • FIG. 1 two fuel cells are connected and two short-circuit parts are mounted, which are exemplary, and more fuel cells and short-circuit parts may be disposed.
  • the two fuel cells are referred to as a first fuel cell 11 and a second fuel cell 12 , respectively.
  • the two shorting parts are referred to as a first shorting part 41 and a second shorting part 45 .
  • the first short circuit part 41 includes the first short circuit switch 43 and the first short circuit resistor 42
  • the second short circuit part 45 includes the second short circuit switch 47 and the second short circuit resistor 46 .
  • FET Field Effect Transistor
  • the short circuit unit 40 is not operated frequently, but is operated under specific conditions.
  • the current and voltage of the fuel cell 10 are measured by the current sensor and the voltage sensor constituting the state detection unit 100, and the actual power value is calculated using the software through the I-V curve.
  • the measured actual power value of the fuel cell 10 is compared with a preset power Ref value. If the actual power value of the fuel cell 10 is smaller than the preset power Ref value, this means that the platinum (Pt) catalyst is oxidized on the surface of the fuel cell 10 and the oxide is excessive on the surface of the reaction area of hydrogen and oxygen This may be due to a decrease in power.
  • the short circuit unit 40 is operated and the cathode terminal (+) and the anode terminal (-) are short-circuited. make it
  • a high current load 90 that is, a current pulse is applied to the fuel cell 10 , so that the fuel The oxide on the surface of the cell 10 is removed, and the effect of forming a hydration region in the fuel cell 10 is obtained.
  • a hydration region is generated in a membrane electrode assembly (MEA) and a gas diffusion layer (GDL), so that drying can be alleviated. Also, the reaction humidity condition of hydrogen and oxygen is created, and the reaction force is recovered, so that the output of the fuel cell can be recovered or further improved.
  • MEA membrane electrode assembly
  • GDL gas diffusion layer
  • the battery 80 when the fuel cell 10 is reactivated by the operation of the short circuit unit 40 , the battery 80 supplies power to the load 90 to prevent a power gap.
  • the battery 80 functions as an auxiliary power source and supplies power to the drone during the time the fuel cell 10 is reactivated. to maintain a stable flight of
  • a supplementary description of the method of generating a current pulse in the short circuit part 40 will use a field effect transistor (FET) as the short circuit part 40 to short-circuit the fuel cell 10, thereby generating a high current of about 270A. and the voltage of the fuel cell 10 drops to 0V.
  • FET field effect transistor
  • This operation is performed for about 0.1 seconds, and the stack voltage is fully recovered after 0.05 seconds. That is, it takes a total of 0.15 seconds until a current pulse is generated using a field effect transistor (FET) and the fuel cell 10 recovers a normal state.
  • FET field effect transistor
  • the current generated by short-circuiting the fuel cell 10 is generated up to a maximum of 330A depending on the performance of the fuel cell 10 .
  • a current of 300 A or more causes a reverse potential of the fuel cell 10 to cause deterioration.
  • the short circuit resistance is added to the field effect transistor (FET) to limit the maximum current that can be generated so that deterioration does not occur.
  • the method of checking the performance of the fuel cell that is, the method of calculating the actual measured power value
  • the fuel cell Since the fuel cell has a characteristic that the voltage value and the current value change according to the load 90 , it can be utilized. .
  • the voltage and current are measured with a voltage sensor and current sensor, the actual measured power value is obtained, and then compared with the expected power value (Ref). It is judged that the performance is good, and the current pulse operation is omitted. Conversely, when the measured power value is less than the expected power value Ref, it is determined that the performance of the fuel cell is bad and a current pulse operation is performed.
  • An additional operation method of the short circuit unit 40 is as follows.
  • the plurality of short circuits do not operate at the same time.
  • two fuel cells 11 and 12 are connected in a circuit.
  • FIG. 1 The embodiment shown in FIG. 1 is for convenience of description, and a plurality of fuel cells may be connected in a circuit according to design specifications. That is, it is not necessary to limit the number of fuel cells shown in FIG. 1 . )
  • the first The first short-circuit unit 41 may operate to apply a current pulse to the first fuel cell 11 and form a hydration region.
  • the second short circuit part 45 does not operate, and power may be continuously supplied to the load 90 while the first fuel cell 11 performs reactivation.
  • the smallest actual measured power value among the plurality of short circuits connected to the plurality of fuel cells is It can operate sequentially from any one short circuit connected to any one calculated fuel cell.
  • two fuel cells 11 and 12 are connected in a circuit.
  • the first fuel cell 11 is preferentially reactivated will be needed
  • the first short circuit unit 41 operates preferentially to apply a current pulse to the first fuel cell 11 and form a hydration region.
  • the second short circuit part 45 does not operate, and power may be continuously supplied to the load 90 while the first fuel cell 11 performs reactivation.
  • the second short circuit part 45 operates next to apply a current pulse to the second fuel cell 12 and form a hydration region.
  • the first fuel cell 11 that has been reactivated may supply power to the load 90 . If power supply to the load 90 is insufficient, power may be supplied in parallel from the battery 80 .
  • the high output mode F1 may be a control mode that is disposed in the control module P and supplies high output power from the fuel cell 10 to the load 90 .
  • the high power means that a relatively high power is transmitted with respect to a low power.
  • the first and second fuel cells 11 and 12 are directly connected to a load 90 in a circuit form in the high output mode F1 . Accordingly, the outputs of the first and second fuel cells 11 and 12 may be directly transferred to the load 90 without conversion. In this case, high power is transmitted to the drone.
  • First and second current sensors 51 and 52 may be disposed between the first and second fuel cells 11 and 12 and the load 90 .
  • the current sensor may be a CT sensor (Current Transformer sensor).
  • the current sensor used in the present invention is basically insulated, may be a current measuring method using a Hall sensor, and may be used to measure the current of a high power system. That is, in the embodiment of the present invention, it may be configured on a circuit for the purpose of measuring high currents of the first and second fuel cells 11 and 12 .
  • the fourth current sensor 54 may also be disposed on a circuit connected to the load 90 .
  • first and second diodes 61 and 62 may be disposed between the first and second fuel cells 11 and 12 and the load 90 .
  • diodes are disposed in a circuit for the purpose of allowing current to flow in one direction.
  • the first and second diodes 61 and 62 used in the embodiment of the present invention are the voltage and current of the battery 80 as fuel. It may be disposed for the purpose of preventing the battery 10 from being affected.
  • second and fourth switches 72 and 74 may be disposed between the first and second fuel cells 11 and 12 and the load 90 , which is an operating condition for adjusting the power supplied or any one According to a specific condition such as a malfunction, the fourth switch 74 is opened when only the first fuel cell 11 is to be used, and when only the second fuel cell 12 is intended to be used, the second switch 72 is turned on. open up
  • the second and fourth switches 72 and 74 are closed so that high power is supplied from the first and second fuel cells 11 and 12 to the load 90 . have.
  • first, second, and third Zener diodes 66, 67, and 68 may be disposed.
  • a Zener diode is a type of diode and is also called a constant voltage diode. It has the same characteristics as a general diode in the forward direction, but when a voltage is applied in the reverse direction, a reverse current flows at a specific voltage (breakdown voltage or Zener voltage).
  • a Zener diode (or TVS) may be used to suppress a rise of a predetermined voltage or more.
  • the low output mode (F2) is disposed in the control module (P), the fuel cell (10) to the load (90) a control for supplying a relatively low low output power compared to the high output mode (F1) can be a mode.
  • a converter unit 30 for converting an output is connected between the fuel cell 10 and the load 90 , and the converter unit 30 is connected to the It may be configured to convert a high voltage into a low voltage and supply it to the load 90 .
  • the converter unit 30 used in the present invention may be a DC-DC converter.
  • the battery 80 may charge and store electric power, and supply electric power to the load 90 together with the fuel cell 10 in an auxiliary or parallel manner.
  • a third current sensor 53 may also be disposed on a circuit connected to the battery 80 .
  • the converter unit 30 may convert power of the fuel cell 10 and supply it to the battery 80 to charge the battery 80 .
  • the first and third switches 71 and 73 may be disposed between the first and second fuel cells 11 and 12 and the converter unit 30 , which are operated under any one of the operating conditions for adjusting the power supplied.
  • the first switch 71 is opened, and when only the second fuel cell 12 is to be used, the third switch 73 is turned on. open up
  • a third diode 63 may be disposed between the converter unit 30 and the load 90 or the battery 80 , and the third diode 63 is a rectifier, which is converted by the converter unit 30 . It allows the current to flow in one direction, that is, in the direction of the load 90 or the battery 80 without reverse flow.
  • fifth and sixth switches 75 and 76 are disposed on the circuit between the converter unit 30 and the battery 80 and the load 90 to control the current supply, and also a fifth current sensor 55 ) can be placed. Also, a fourth diode 64 may be disposed for the forward flow of current.
  • a plurality of converter units 30 may be disposed, and the plurality of converters may be circuitly connected to a plurality of fuel cells.
  • the present invention is not limited thereto.
  • various negative electrodes may be connected to the case ground.
  • FIG. 2 is a diagram illustrating power flows in a high output mode (F1) and a low output mode (F2) in the power control system of a fuel cell according to the present invention.
  • FIG. 3 is a graph showing the relationship between the power operation of the fuel cell power control system of the present invention and the operation of the drone.
  • path A in the case of path A, it may be a mode in which power is supplied in a low output mode F2. And in the case of the B path, it may be a mode in which power is supplied in the high output mode F1.
  • the high output mode F1 means that relatively higher power is supplied than that of the low output mode F2, and on the contrary, the low output mode F2 means that relatively lower power is supplied than that of the high output mode F1, so they are relative values.
  • I-V CURVE is a power graph expressed based on the current and voltage measured by the fuel cell 10 .
  • the A route operation area A represents a power state graph at the time of takeoff, landing, and initial startup of the drone.
  • the power state graph in the 'standby state' from the start of the drone to before flight may be displayed.
  • the B route operation area (B) represents the power state graph while the drone is flying.
  • the meaning of the initial maneuver of the drone may mean a state in which the drone is floating in the air after take-off and before moving in a specific direction
  • the meaning of the flight maneuver of the drone may mean a state of moving in earnest in a specific direction.
  • the control module (P) When the operator first transmits the takeoff signal of the drone through the controller, the control module (P) performs power supply on the A path. At this time, the drone is ready for takeoff and initial maneuver.
  • the second and fourth switches 72 and 74 are opened, and the first, third, and sixth switches 71, 73 and 76 are closed.
  • Power is supplied from the first and second fuel cells 11 and 12 to the first and second converters 31 and 32 .
  • the first and second converters 31 and 32 convert the power of the fuel cell 10 to make it relatively low-output.
  • the low power mode (F2) is performed, the converted power is supplied to the drone, and the drone takes off.
  • control module (P) automatically performs B-path power supply.
  • the first and third switches 71 and 73 are opened, and the second and fourth switches 72 and 74 are closed. Since the sixth switch 76 may receive power from the battery 80 , it maintains a closed state. Now, power from the first and second fuel cells 11 and 12 is directly supplied to the drone along the B path. Since power is not converted in the first and second converters 31 and 32 , power in a high-output state is supplied to the drone, and sufficient power is supplied between flight maneuvers of the drone.
  • the power gap area X and the actual flight possible area Y are shown in the B route driving area B disclosed in FIG. 3 .
  • the power gap area (X) there is a difference in power between the power required for the drone takeoff and the power required for the drone's flight maneuver. indicates
  • control module (P) supplies high output power in the B route, the difference in power between the power required for takeoff of the drone and the power required for starting the flight of the drone after a certain point in time is filled, and the power required for the actual maneuvering flight of the drone to reach That is, it reaches the high output power value of the actual flight possible area (Y).
  • control module P performs power supply of route A again.
  • the second and fourth switches 72 and 74 are opened, and the first and third switches 71 and 73 are closed.
  • the sixth switch 76 remains closed. Thereafter, power is supplied from the first and second fuel cells 11 and 12 to the first and second converters 31 and 32 .
  • the first and second converters 31 and 32 convert the power of the fuel cell 10 to make it relatively low-output. Low power mode (F2) is performed, the converted power is supplied to the drone, and the drone lands.
  • low power is supplied in the low output mode (F2) of the A route during takeoff and landing or initial maneuvering of the drone, and high power is supplied in the high output mode (F1) of the B route when the drone is flying.
  • FIG. 4 shows the battery 80 together with the high output mode F1 of the fuel cell 10 when a voltage drop occurs due to an overload in the fuel cell 10 in the power control system of the fuel cell according to the present invention. It is a diagram showing the power supply through.
  • control module P closes the sixth switch 76 so that the current of the battery 80 passes through the fourth diode 64 and then is supplied to the drone (C path). In this case, the battery 80 is gradually discharged because the stored power is supplied to the drone.
  • the power supply continues through the high output mode F1 and the insufficient power is supplied in parallel through the battery 80, This is to ensure that power can be stably supplied between the flight maneuvers of the drone even in an emergency situation.
  • FIG. 5 is a diagram illustrating a power flow for charging the battery 80 by converting the power of the fuel cell 10 in the converter unit 30 when the drone is flying in the fuel cell power control system according to the present invention.
  • an operator may control charging of the battery 80 through the controller 20 and detect whether current is properly flowing to the battery 80 .
  • the first and third switches 71 and 73 are closed to charge the battery 80 and power of the fuel cell 10 is supplied to the converter unit 30 .
  • the power converted by the converter unit 30 flows along the D path and charges the battery 80 .
  • the controller 20 may transmit the battery 80 charging signal to the converter unit 30 through the battery 80 charging signal line 21 , and the battery 80 charging signal through the current detection signal line 22 . You can receive the charging status.
  • charging of the battery 80 is performed after power conversion in the converter by utilizing the low output mode F2.
  • the charging of the battery 80 during flight of the drone may utilize the low power mode F2 of the A path. Since the voltage rises when the battery 80 is charged, the converter unit 30 must be used to respond to this and prevent excessive charging current from occurring during charging. Accordingly, the low output mode F2 of the A path in which the converter unit 30 is disposed is utilized.
  • the present invention can efficiently operate power by applying a control method that utilizes the low output mode F2 of the A path so that the battery 80 can be charged even during flight of the drone.
  • FIG. 6 is a view showing another form of the converter unit 30 in the power control system of the fuel cell according to the present invention disclosed in FIG. 1 .
  • the converter unit 30 includes a first converter 31 , a master converter, a second converter 32 , a slave converter, and the first and second converters 31 and 32 .
  • ) may have a structure that is circuitly connected to the converter connection line 34 .
  • the first converter 31 may mainly perform power conversion
  • the second converter 32 may auxiliary power conversion according to design conditions.
  • FIG. 7 is a view showing another form of the converter unit 30 in the power control system of the fuel cell according to the present invention disclosed in FIG. 1 .
  • the converter unit 30 may be a single converter 35 integrally connected to the cathode terminals of the plurality of fuel cells, respectively.
  • the present invention relates to a fuel cell and has industrial applicability.

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Abstract

La présente invention concerne un système et un procédé de commande de la puissance d'une pile à combustible. Le système peut être conçu pour comprendre : une pile à combustible pour générer une puissance et comprenant une borne de cathode et une borne d'anode au niveau d'une extrémité de sortie ; un module de commande pour commander une alimentation électrique entre la pile à combustible et une puissance de consommation de charge ; un mode de sortie élevée du module de commande, dans lequel une puissance de sortie élevée est fournie de la pile à combustible à la charge ; et un mode de sortie faible du module de commande, dans lequel une puissance de sortie faible est fournie de la pile à combustible à la charge, la puissance de sortie faible étant relativement inférieure à la puissance de sortie élevée. Selon la présente invention, l'efficacité de fonctionnement de puissance peut être améliorée par fourniture d'une puissance à partir de la pile à combustible dans le mode de sortie faible lorsqu'un drone décolle et atterrit ou démarre, et par fourniture d'une puissance à partir de la pile à combustible dans le mode de sortie élevée lorsque le drone vole.
PCT/KR2021/008344 2020-07-24 2021-07-01 Système et procédé de commande de la puissance d'une pile à combustible WO2022019517A1 (fr)

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