Power supply device, flying tool using same and power supply method thereof

A power supply device disposed on an aircraft to provide a power to the aircraft, wherein the aircraft has an average required power value, and the power supply device comprises:

• a secondary battery;
• a first transformer coupled between the secondary battery and the aircraft;
• and
• a fuel cell coupled to the aircraft and adapted to provide a first output current to the aircraft;
• wherein the first transformer has an output voltage set value, and provides a second output current of the secondary battery to the aircraft when a first output end voltage of the fuel cell is lower than the output voltage set value;
• wherein the output voltage set value is in a voltage range with a fuel cell output power between the maximum power value of a characteristic curve of the fuel cell and the average required power value of the aircraft;
• wherein the power supply device further comprises:
• a second transformer coupled between the fuel cell and the secondary battery, wherein the second transformer has an input voltage set value higher than the output voltage set value of the first transformer;
• wherein when the first output end voltage of the fuel cell is equivalent to or higher than the input voltage set value, the fuel cell charges the secondary battery.

A flying tool, comprising:

• an aircraft having an average required power value;
• and
• a power supply device disposed on the aircraft to provide a power to the aircraft and comprising:
• a secondary battery;
• a first transformer coupled between the secondary battery and the aircraft;
• and
• a fuel cell coupled to the aircraft and adapted to provide a first output current to the aircraft;
• wherein the first transformer has an output voltage set value, and provides a second output current of the secondary battery to the aircraft when a first output end voltage of the fuel cell is lower than the output voltage set value;
• wherein the output voltage set value is in a voltage range with a fuel cell output power between the maximum power value of a characteristic curve of the fuel cell and the average required power value of the aircraft;
• wherein the power supply device further comprises a switch coupled between an output end of the secondary battery and an output end of the fuel cell, and the switch is connected and causes the fuel cell to charge the secondary battery when the first output end voltage is equivalent to or higher than a second output end voltage at the output end of the secondary battery.

A power supply method of a power supply device, wherein the power supply device is disposed on an aircraft and comprises a secondary battery, a first transformer and a fuel cell;

• the secondary battery is coupled to the aircraft through the first transformer having an output voltage set value;
• the power supply method comprises:
• providing a first output current to the aircraft by the fuel cell;
• and
• providing a second output current of the secondary battery to the aircraft by the first transformer when a first output end voltage of the fuel cell is lower than the output voltage set value;
• wherein the output voltage set value is in a voltage range with a fuel cell output power between the maximum power value of a characteristic curve of the fuel cell and the average required power value of the aircraft;
• wherein the power supply device further comprises a switch coupled between an output end of the secondary battery and an output end of the fuel cell, and the power supply method further comprises:
• connecting the switch and causing the fuel cell to charge the secondary battery when the first output end voltage is equivalent to or higher than a second output end voltage at the output end of the secondary battery.

A power supply method of a power supply device, wherein the power supply device is disposed on an aircraft and comprises a secondary battery, a first transformer and a fuel cell;

• the secondary battery is coupled to the aircraft through the first transformer having an output voltage set value;
• the power supply method comprises:
• providing a first output current to the aircraft by the fuel cell;
• and
• providing a second output current of the secondary battery to the aircraft by the first transformer when a first output end voltage of the fuel cell is lower than the output voltage set value;
• wherein the output voltage set value is in a voltage range with a fuel cell output power between the maximum power value of a characteristic curve of the fuel cell and the average required power value of the aircraft;
• wherein the power supply device further comprises a second transformer having an input voltage set value higher than the output voltage set value of the first transformer;
• the power supply method further comprising:
• charging the secondary battery by the fuel cell when the first output end voltage of the fuel cell is equivalent to or higher than the input voltage set value.