Power supply system of aircraft and control method thereof
A power supply system for an aircraft and a control method thereof are provided. The power supply system of the aircraft includes a fuel cell configured to generate electrical energy, a converter device configured to supply a voltage generated by the fuel cell to a first motor device for driving the aircraft through a first output terminal and switch a connection with the fuel cell depending on a predetermined driving mode, a battery configured to supply the voltage to a second motor device for driving the aircraft through a second output terminal, the second output terminal being connected with an output node of the fuel cell, and a processor configure to control a connection between the fuel cell and the converter device depending on the driving mode.
1. A power supply system for an aircraft, the power supply system comprising:
a fuel cell configured to generate a voltage;
a converter device configured to:
supply, through a first output terminal of the power supply system, the voltage generated by the fuel cell to a first motor device for driving the aircraft; and
switch, based on a predetermined driving mode, a connection between the fuel cell and the converter device;
a battery configured to supply, through a second output terminal of the power supply system, a voltage to a second motor device for driving the aircraft, the second output terminal being connected with an output node of the fuel cell; and
a processor configured to control the connection between the fuel cell and the converter device depending on the predetermined driving mode,
wherein the converter device comprises:
a first converter switch and a second converter switch, connected in series with each other, between the first output terminal and a reference node;
a first inductor connected with a node between the first converter switch and the second converter switch; and
a mode switch device configured to electrically connect the first inductor with the output node of the fuel cell or with the second output terminal.
2. The power supply system of claim 1 , wherein
the mode switch device is configured to be controlled by the processor to selectively connect the first inductor with the output node of the fuel cell or disconnect the first inductor from the output node of the fuel cell.
3. The power supply system of claim 1 , wherein the processor is configured to control the mode switch device, such that the predetermined driving mode is a first mode, to connect the first inductor with the output node of the fuel cell, based on a determination that an altitude of the aircraft is less than a predetermined first threshold altitude after the aircraft is turned on.
4. The power supply system of claim 3 , wherein the processor is configured to control the mode switch device, such that the predetermined driving mode is a second mode, to disconnect the first inductor from the output node of the fuel cell, based on a determination that the aircraft ascends above the first threshold altitude.
5. The power supply system of claim 4 , wherein the processor is configured to control the mode switch device, such that the predetermined driving mode is the first mode, based on a determination that the aircraft descends below a predetermined second threshold altitude.
6. The power supply system of claim 4 , wherein the mode switch device is configured to be controlled by the processor to connect the first inductor with the second output terminal in the second mode.
7. The power supply system of claim 6 , wherein the mode switch device is a single pole double throw (SPDT) relay configured to be controlled by the processor to connect the first inductor with the output node of the fuel cell or the second output terminal.
8. The power supply system of claim 6 , wherein the mode switch device comprises:
a mode switch configured to connect the first inductor with the output node of the fuel cell in the first mode; and
an auxiliary mode switch configured to connect the first inductor with the second output terminal in the second mode.
9. The power supply system of claim 8 , wherein the mode switch and the auxiliary mode switch are complementary to each other in operation timing.
10. The power supply system of claim 6 , further comprising:
a first auxiliary converter switch and a second auxiliary converter switch, connected in series with each other, between the second output terminal and the reference node,
wherein the mode switch device is configured to connect a node between the first auxiliary converter switch and the second auxiliary converter switch with the first inductor.
11. The power supply system of claim 10 , wherein the processor is configured to set a turn-on duty ratio of the first converter switch and the first auxiliary converter switch to determine a magnitude of a voltage distributed to the second output terminal.
12. The power supply system of claim 6 , wherein the converter device further comprises:
a first link capacitor connected in parallel with the fuel cell; and
a second link capacitor connected between the first output terminal and the reference node.
13. The power supply system of claim 1 , wherein the converter device further comprises:
a third converter switch and a fourth converter switch connected in series with each other between the first output terminal and a reference node; and
a second inductor connected with a node between the third converter switch and the fourth converter switch.
14. The power supply system of claim 13 , wherein the second inductor is configured to maintain a state where the second output terminal is connected with the output node of the fuel cell.
15. A control method for a power supply system of an aircraft, the control method comprising:
supplying, by a converter device of the power supply system, a first voltage of a fuel cell to a first motor device through a first output terminal of the power supply system in a first mode of the power supply system;
supplying, by a battery device of the power supply system, a second voltage to a second motor device through a second output terminal of the power supply system; and
connecting, by the converter device, the first output terminal with the second output terminal to charge the battery device using the first voltage output by the fuel cell, such that the power supply system operates in a second mode, based on a determination that the aircraft ascends above a predetermined first threshold altitude,
wherein the connecting of the first output terminal and the second output terminal comprises:
providing an output of a half-bridge converter to the second output terminal, wherein the half-bridge converter comprises:
a first converter switch;
a second converter switch; and
an inductor, wherein the first converter switch, the second converter switch, and the inductor are formed between the first output terminal and a reference node.
16. The control method of claim 15 , further comprising:
disconnecting the second output terminal from the first output terminal and operating in the first mode, based on a determination that the aircraft descends below a predetermined second threshold altitude.
17. The control method of claim 15 , wherein the connecting of the first output terminal and the second output terminal comprises:
disconnecting a connection between the inductor and an output node of the fuel cell; and
connecting the inductor with the second output terminal.
18. The control method of claim 15 , wherein the connecting of the first output terminal and the second output terminal comprises:
providing an output of an H bridge converter, wherein the H bridge converter comprises:
the half-bridge converter;
a first auxiliary converter switch connected with the half-bridge converter and the second output terminal; and
a second auxiliary converter switch connected with the half-bridge converter and the second output terminal.
19. A power supply system for an aircraft, the power supply system comprising:
a fuel cell configured to generate a voltage;
a converter device configured to:
supply, through a first output terminal of the power supply system, the voltage generated by the fuel cell to a first motor device for driving the aircraft; and
switch, based on a predetermined driving mode, a connection between the fuel cell and the converter device;
a battery configured to supply, through a second output terminal of the power supply system, a voltage to a second motor device for driving the aircraft, the second output terminal being connected with an output node of the fuel cell; and
a processor configured to control the connection between the fuel cell and the converter device depending on the predetermined driving mode,
wherein the converter device comprises:
a first inductor; and
a mode switch device configured to be controlled by the processor to selectively connect the first inductor with the output node of the fuel cell,
wherein the processor is configured to control the mode switch device, such that the predetermined driving mode is a second mode, to disconnect the first inductor from the output node of the fuel cell, and
wherein the mode switch device is configured to be controlled by the processor to electrically connect the first inductor with the second output terminal in the second mode.