Oxygen supply apparatus and method for fuel cell of aircraft

Patent metadata

Field	Value
Publication number	US-11799107-B2
Application number	US-202117501966-A
Country	US
Kind code	B2
Filing date	Oct 14, 2021
Priority date	Jan 18, 2021
Publication date	Oct 24, 2023
Grant date	Oct 24, 2023

Abstract

An oxygen supply apparatus and method for a fuel cell of an aircraft are provided. The oxygen supply apparatus includes a compressor that generates compressed air by compressing air in the atmosphere and supplies the compressed air to a fuel cell stack, an oxygen tank having a predetermined amount of oxygen stored therein. An aircraft monitoring device monitors the aircraft and determines whether oxygen supply from the oxygen tank is required, and an oxygen supply means switching device switches an oxygen supply means for the fuel cell stack from the compressor to the oxygen tank, or vice versa depending on an outcome of the monitoring.

First claim

What is claimed is:

1. An oxygen supply apparatus for a fuel cell of an aircraft, the oxygen supply apparatus comprising:
a compressor configured to generate compressed air by compressing air in the atmosphere and supply the compressed air to a fuel cell stack;
an oxygen tank having a predetermined amount of oxygen stored therein;
an aircraft monitoring device configured to monitor the aircraft and determine whether oxygen supply from the oxygen tank is required; and
an oxygen supply means switching device configured to switch an oxygen supply means for the fuel cell stack from the compressor to the oxygen tank depending on an outcome of the monitoring
wherein the aircraft monitoring device includes:
a flight altitude determination device configured to determine whether to change the oxygen supply means depending on a change in a flight altitude of the aircraft so as to supply the compressed air to the fuel cell stack by the compressor when the flight altitude of the aircraft is lower than a preset reference altitude, or to supply the oxygen stored in the oxygen tank to the fuel cell stack when the flight altitude of the aircraft is higher than the reference altitude.

2. The oxygen supply apparatus of claim 1 , wherein the flight altitude determination device includes:
an altitude comparator configured to receive a current flight altitude from an altimeter provided in the aircraft and compare the current flight altitude with the preset reference altitude.

3. The oxygen supply apparatus of claim 1 , wherein the flight altitude determination device includes:
a cell voltage comparator configured to estimate the flight altitude of the aircraft by comparing the average of cell voltages measured by a stack voltage monitoring (SVM) device provided in the fuel cell with a preset reference voltage.

4. The oxygen supply apparatus of claim 3 , wherein the cell voltage comparator is configured to estimate that the aircraft flies at an altitude lower than the reference altitude, when the average of the cell voltages measured by the stack voltage monitoring device is greater than the reference voltage, and the cell voltage comparator is configured to estimate that the aircraft flies at an altitude higher than the reference altitude, when the average of the cell voltages is less than the reference voltage.

5. The oxygen supply apparatus of claim 1 , wherein the aircraft monitoring device includes:
a flight mode determination device configured to determine whether a flight mode of the aircraft is a cruising mode or a taking-off/landing mode and determine whether to change the oxygen supply means depending on a change in the flight mode of the aircraft, such that when the flight mode is the cruising mode, the compressed air is supplied to the fuel cell stack by the compressor, and when the flight mode is the taking-off/landing mode, the oxygen stored in the oxygen tank is supplied to the fuel cell stack.

6. The oxygen supply apparatus of claim 5 , wherein the flight mode determination device includes:
an altitude change comparator configured to calculate an altitude change of the aircraft for a predetermined reference period of time, compare an absolute value of the calculated altitude change with a preset reference altitude change, determine that the aircraft is in the cruising mode when the absolute value of the calculated altitude change is less than the reference altitude change, and determine that the aircraft is in the taking-off/landing mode when the absolute value of the calculated altitude change is greater than the reference altitude change.

7. The oxygen supply apparatus of claim 5 , wherein the flight mode determination device includes:
a wing shape determination device configured to determine that the aircraft is in the cruising mode when a flap of a wing of the aircraft is in a neutral state and determine that the aircraft is in the taking-off/landing mode when the flap of the wing of the aircraft is in a flat state.

8. The oxygen supply apparatus of claim 1 , wherein the aircraft monitoring device includes:
an output power comparator configured to compare an output power requirement that has to be generated in the fuel cell for operation of the aircraft with preset reference output power and determine whether to change the oxygen supply means depending on a change in the output power requirement that has to be generated in the fuel cell to supply the compressed air to the fuel cell stack by the compressor when the output power requirement is less than the reference output power and the oxygen stored in the oxygen tank is supplied to the fuel cell stack when the output power requirement is greater than the reference output power.

9. The oxygen supply apparatus of claim 1 , wherein the oxygen supply means switching device includes:
a valve switching controller configured to execute selective opening/closing of a compressed-air supply valve and a pure oxygen supply valve depending on a determination result of the aircraft monitoring device,
wherein the compressed-air supply valve is provided at an output end from which the compressed air generated by the compressor is supplied, and the pure oxygen supply valve is provided at an output end from which the oxygen stored in the oxygen tank is supplied.

10. The oxygen supply apparatus of claim 9 , wherein the valve switching controller is configured to switch the oxygen supply means for the fuel cell stack by opening one of the compressed-air supply valve and the pure oxygen supply valve and closing the remaining valve.

11. The oxygen supply apparatus of claim 1 , wherein the compressor is implemented with a shut-off type compressor configured to, when turned off, automatically close a path along which air is movable, and wherein the oxygen supply means switching device includes:
a compressor OFF controller configured to change the oxygen supply means for the fuel cell stack by turning off the compressor while opening a pure oxygen supply valve provided at an output end from which the oxygen stored in the oxygen tank is supplied, or by closing the pure oxygen supply valve while turning on the compressor, depending on a determination result of the aircraft monitoring device.

12. An oxygen supply apparatus for a fuel cell of an aircraft, the oxygen supply apparatus comprising:
a compressor configured to generate compressed air by compressing air in the atmosphere and supply the compressed air to a fuel cell stack;
an oxygen tank having a predetermined amount of oxygen stored therein and including a pure oxygen supply valve configured to adjust whether to supply the oxygen, wherein an oxygen supply path is connected to a compressed-air supply path extending from the compressor to the fuel cell stack;
an aircraft monitoring device configured to monitor the aircraft and determine whether oxygen supply from the oxygen tank is required; and
an additional oxygen supply controller configured to adjust whether to open or close the pure oxygen supply valve, depending on a monitoring result and perform control such that oxygen supplied to the fuel cell stack is only the compressed air, or a mixture of the compressed air and the oxygen,
wherein the additional oxygen supply controller is configured to consistently maintain the supply of the compressed air from the compressor to the fuel cell stack and additionally supply the predetermined amount of oxygen to the compressed-air supply path when a flight altitude of the aircraft is higher than a preset reference altitude.

13. The oxygen supply apparatus of claim 12 , wherein the additional oxygen supply controller is configured to consistently maintain the supply

Assignees

• Hyundai Motor Co Ltd
• Kia Corp

Inventors

• Lee Joung Ho
• Lee Nam Woo
• Yoon Hee Sung

Classifications

• B64D27/355

  using fuel cells · CPC title

• H01M8/04753 Primary

  of fuel cell reactants · CPC title

• B64D37/30 Primary

  Fuel systems for specific fuels · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• H01M8/04089 Primary

  of gaseous reactants · CPC title