Airborne liquid hydrogen storage and supply system

Abstract

The invention relates to an airborne liquid hydrogen storage and supply system which comprises a first liquid hydrogen supply module, a first gas hydrogen supply module, a second liquid hydrogen storage and supply module and a second gas hydrogen supply module, and the first liquid hydrogen storage and supply module comprises the first liquid hydrogen supply module and the first gas hydrogen supply module. The first liquid hydrogen supply module comprises a first liquid hydrogen storage tank, a first liquid hydrogen pipeline, a first liquid hydrogen storage tank outlet valve, a second liquid hydrogen pipeline, a first power pump module and a third liquid hydrogen pipeline; the second liquid hydrogen supply module comprises a second liquid hydrogen supply module and a second gas hydrogen supply module; the second liquid hydrogen supply module comprises a second liquid hydrogen storage tank, a fourth liquid hydrogen pipeline, a second liquid hydrogen storage tank outlet valve, a fifth liquid hydrogen pipeline, a second power pump module and a sixth liquid hydrogen pipeline; the first control valve is arranged between the third liquid hydrogen pipeline and the sixth liquid hydrogen pipeline; and the second control valve is arranged between the first liquid hydrogen pipeline and the fourth liquid hydrogen pipeline.

Description

Technical Field

[0001] This invention relates to the field of liquid hydrogen application technology, and more specifically to an airborne liquid hydrogen storage and supply system. Background Technology

[0002] The development of aerial platforms such as hydrogen-fueled drones, low-altitude rotary-wing aircraft, and large aircraft is one of the important development directions for low-carbon, environmentally friendly, and advanced aviation technologies.

[0003] Liquid hydrogen has a high hydrogen storage-to-weight ratio, giving it a natural advantage in meeting the requirements for lightweight airborne equipment. Aviation has extremely stringent safety requirements. Based on a comprehensive consideration of safety and economy, it is necessary to ensure that the liquid hydrogen storage and supply system can still provide the necessary hydrogen to the aircraft engines in the event of a failure. However, existing liquid hydrogen storage and supply systems are difficult to achieve this. Summary of the Invention

[0004] To address the shortcomings of existing technologies, this invention provides an airborne liquid hydrogen storage and supply system, aiming to solve the problem that existing liquid hydrogen storage and supply systems cannot guarantee the supply of hydrogen to aircraft engines in the event of a malfunction.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] An airborne liquid hydrogen storage and supply system, comprising:

[0007] A first liquid hydrogen storage and supply module includes a first liquid hydrogen supply module and a first gaseous hydrogen supply module. The first liquid hydrogen supply module includes a first liquid hydrogen storage tank, a first liquid hydrogen pipeline, a first liquid hydrogen storage tank outlet valve, a second liquid hydrogen pipeline, a first power pump module, and a third liquid hydrogen pipeline. The outlet of the first liquid hydrogen storage tank is connected to a first end of the first liquid hydrogen pipeline, the second end of the first liquid hydrogen pipeline is connected to the inlet of the first liquid hydrogen storage tank outlet valve, one end of the second liquid hydrogen pipeline is connected to the outlet of the first liquid hydrogen storage tank outlet valve, the other end of the second liquid hydrogen pipeline is connected to the inlet of the first power pump module, the outlet of the first power pump module is connected to the inlet of the third liquid hydrogen pipeline, and the outlet of the third liquid hydrogen pipeline is connected to the first gaseous hydrogen supply module. The first gaseous hydrogen supply module is used to heat liquid hydrogen to vaporize it into hydrogen gas to supply the first engine of the aircraft.

[0008] The second liquid hydrogen storage and supply module includes a second liquid hydrogen supply module and a second gaseous hydrogen supply module. The second liquid hydrogen supply module includes a second liquid hydrogen storage tank, a fourth liquid hydrogen pipeline, a second liquid hydrogen storage tank outlet valve, a fifth liquid hydrogen pipeline, a second power pump module, and a sixth liquid hydrogen pipeline. The outlet of the second liquid hydrogen storage tank is connected to the first end of the fourth liquid hydrogen pipeline, the second end of the fourth liquid hydrogen pipeline is connected to the inlet of the second liquid hydrogen storage tank outlet valve, one end of the fifth liquid hydrogen pipeline is connected to the outlet of the second liquid hydrogen storage tank outlet valve, the other end of the fifth liquid hydrogen pipeline is connected to the inlet of the second power pump module, the outlet of the second power pump module is connected to the inlet of the sixth liquid hydrogen pipeline, and the outlet of the sixth liquid hydrogen pipeline is connected to the second gaseous hydrogen supply module. The second gaseous hydrogen supply module is used to heat liquid hydrogen to vaporize it into hydrogen gas to supply the second engine of the aircraft.

[0009] A first control valve is disposed between the third liquid hydrogen pipeline and the sixth liquid hydrogen pipeline, and is used to control the connection between the third liquid hydrogen pipeline and the sixth liquid hydrogen pipeline;

[0010] A second control valve is disposed between the first liquid hydrogen pipeline and the fourth liquid hydrogen pipeline, and is used to control the connection between the first liquid hydrogen pipeline and the fourth liquid hydrogen pipeline.

[0011] Further, the first power pump module includes: a first liquid hydrogen pump inlet control valve, a first liquid hydrogen pump, a second liquid hydrogen pump inlet control valve, and a second liquid hydrogen pump; the first end of the second liquid hydrogen pipeline is connected to the outlet of the first liquid hydrogen storage tank outlet valve, the second end of the second liquid hydrogen pipeline is connected to the first liquid hydrogen pump through the first liquid hydrogen pump inlet control valve, the third end of the second liquid hydrogen pipeline is connected to the second liquid hydrogen pump through the second liquid hydrogen pump inlet control valve, the first liquid hydrogen pump is connected to the first end of the third liquid hydrogen pipeline, the second liquid hydrogen pump is connected to the second end of the third liquid hydrogen pipeline, and the third end of the third liquid hydrogen pipeline is connected to the first gaseous hydrogen supply module.

[0012] Furthermore, the first liquid hydrogen pump and the second liquid hydrogen pump are centrifugal or plunger-type liquid hydrogen pumps.

[0013] Furthermore, the second power pump module includes: a third liquid hydrogen pump inlet control valve, a third liquid hydrogen pump, a fourth liquid hydrogen pump inlet control valve, and a fourth liquid hydrogen pump; the first end of the fifth liquid hydrogen pipeline is connected to the outlet of the second liquid hydrogen storage tank outlet valve, the second end of the fifth liquid hydrogen pipeline is connected to the third liquid hydrogen pump through the third liquid hydrogen pump inlet control valve, the third end of the fifth liquid hydrogen pipeline is connected to the fourth liquid hydrogen pump through the fourth liquid hydrogen pump inlet control valve, the third liquid hydrogen pump is connected to the first end of the sixth liquid hydrogen pipeline, the fourth liquid hydrogen pump is connected to the second end of the sixth liquid hydrogen pipeline, and the third end of the sixth liquid hydrogen pipeline is connected to the second gaseous hydrogen supply module.

[0014] Furthermore, the third liquid hydrogen pump and the fourth liquid hydrogen pump are centrifugal or plunger-type liquid hydrogen pumps.

[0015] Furthermore, the first gaseous hydrogen supply module includes: a first heater, a first gaseous hydrogen pipeline and a first liquid hydrogen reheating supply pipeline. The inlet of the first heater is connected to the first liquid hydrogen supply module, the outlet of the first heater is connected to the first end of the first gaseous hydrogen pipeline, the second end of the first gaseous hydrogen pipeline is connected to the inlet of the cooling channel of the first engine, the outlet of the cooling channel of the first engine is connected to the first end of the first liquid hydrogen reheating supply pipeline, and the second end of the first liquid hydrogen reheating supply pipeline is connected to the feed port of the first engine.

[0016] The second gaseous hydrogen supply module includes: a second heater, a second gaseous hydrogen pipeline, and a second liquid hydrogen reheating supply pipeline. The inlet of the second heater is connected to the second liquid hydrogen supply module, the outlet of the second heater is connected to the first end of the second gaseous hydrogen pipeline, the second end of the second gaseous hydrogen pipeline is connected to the inlet of the cooling channel of the second engine, the outlet of the cooling channel of the second engine is connected to the first end of the first liquid hydrogen reheating supply pipeline, and the second end of the first liquid hydrogen reheating supply pipeline is connected to the feed port of the second engine.

[0017] Furthermore, the first gaseous hydrogen supply module includes: a first heat exchanger, a first heater, a first gaseous hydrogen pipeline and a first heat pipe. The cold inlet of the first heat exchanger is connected to the first liquid hydrogen supply module, the hot inlet of the first heat exchanger is connected to the outlet of the first heat pipe, the inlet of the first heat pipe is connected to the first engine, the outlet of the first heat exchanger is connected to the inlet of the first heater, the outlet of the first heater is connected to the first end of the first gaseous hydrogen pipeline, and the second end of the first gaseous hydrogen pipeline is connected to the feed port of the first engine.

[0018] The second gaseous hydrogen supply module includes: a second heat exchanger, a second heater, a second gaseous hydrogen pipeline and a second heat pipe. The cold inlet of the second heat exchanger is connected to the second liquid hydrogen supply module, the hot inlet of the second heat exchanger is connected to the outlet of the second heat pipe, the inlet of the second heat pipe is connected to the second engine, the outlet of the second heat exchanger is connected to the inlet of the second heater, the outlet of the second heater is connected to the first end of the second gaseous hydrogen pipeline, and the second end of the second gaseous hydrogen pipeline is connected to the feed port of the second engine.

[0019] Further, the first gaseous hydrogen supply module includes: a first heat exchanger, a first heater, a first centrifugal pump, a first gaseous hydrogen pipeline and a first heat pipe. The cold inlet of the first heat exchanger is connected to the first liquid hydrogen supply module, the hot inlet of the first heat exchanger is connected to the outlet of the first heat pipe, the inlet of the first heat pipe is connected to the first engine, the outlet of the first heat exchanger is connected to the inlet of the first centrifugal pump, the outlet of the first centrifugal pump is connected to the inlet of the first heater, the outlet of the first heater is connected to the first end of the first gaseous hydrogen pipeline, and the second end of the first gaseous hydrogen pipeline is connected to the feed port of the first engine.

[0020] The second gaseous hydrogen supply module includes: a second heat exchanger, a second heater, a second centrifugal pump, a second gaseous hydrogen pipeline, and a second heat pipe. The cold inlet of the second heat exchanger is connected to the second liquid hydrogen supply module, the hot inlet of the second heat exchanger is connected to the outlet of the second heat pipe, the inlet of the second heat pipe is connected to the second engine, the outlet of the second heat exchanger is connected to the inlet of the second centrifugal pump, the outlet of the second centrifugal pump is connected to the inlet of the second heater, the outlet of the second heater is connected to the first end of the second gaseous hydrogen pipeline, and the second end of the second gaseous hydrogen pipeline is connected to the feed port of the second engine.

[0021] Furthermore, the first heat exchanger and the second heat exchanger are aluminum plate heat exchangers or plate-fin heat exchangers.

[0022] The airborne liquid hydrogen storage and supply system described in this invention has the following advantages:

[0023] Under normal operating conditions of the airborne liquid hydrogen storage and supply system, the first and second control valves are closed. Liquid hydrogen is supplied from the first liquid hydrogen supply module to the first gaseous hydrogen supply module. The first gaseous hydrogen supply module heats the liquid hydrogen to vaporize it into hydrogen gas, which is then supplied to the aircraft's first engine. The first gaseous hydrogen supply module recovers the waste heat from the first engine to heat and vaporize the liquid hydrogen, and uses the cooling energy of the liquid hydrogen to cool the first engine. Therefore, no additional cooling equipment is required to cool the first engine. Similarly, liquid hydrogen is supplied from the second liquid hydrogen supply module to the second gaseous hydrogen supply module. The second gaseous hydrogen supply module heats the liquid hydrogen to vaporize it into hydrogen gas, which is then supplied to the aircraft's second engine. The second gaseous hydrogen supply module recovers the waste heat from the second engine to heat and vaporize the liquid hydrogen, and uses the cooling energy of the liquid hydrogen to cool the second engine. Therefore, no additional cooling equipment is required to cool the second engine.

[0024] When the first power pump module of the first liquid hydrogen supply module malfunctions, the first control valve opens, thereby connecting the second liquid hydrogen supply module with the first gaseous hydrogen supply module through the first control valve. The second liquid hydrogen supply module supplies liquid hydrogen to both the first and second gaseous hydrogen supply modules. The first and second gaseous hydrogen supply modules heat the liquid hydrogen to vaporize it into hydrogen gas, which is then supplied to the first and second engines of the aircraft, respectively. Similarly, when the second power pump module of the second liquid hydrogen supply module malfunctions, the first control valve opens, thereby connecting the first liquid hydrogen supply module with the second gaseous hydrogen supply module through the first control valve. The first liquid hydrogen supply module supplies liquid hydrogen to both the first and second gaseous hydrogen supply modules. The first and second gaseous hydrogen supply modules heat the liquid hydrogen to vaporize it into hydrogen gas, which is then supplied to the first and second engines of the aircraft, respectively.

[0025] When the first liquid hydrogen storage tank malfunctions, the outlet valve of the first liquid hydrogen storage tank is closed, the second control valve is opened, and the first hydraulic power pump module draws liquid hydrogen from the second liquid hydrogen storage tank to supply the first gaseous hydrogen supply module; similarly, when the second liquid hydrogen storage tank malfunctions, the outlet valve of the second liquid hydrogen storage tank is closed, the second control valve is opened, and the second power pump module draws liquid hydrogen from the second liquid hydrogen storage tank to supply the second gaseous hydrogen supply module.

[0026] Therefore, the airborne liquid hydrogen storage and supply system of the present invention can still ensure the supply of hydrogen required to the first and second engines of the aircraft when the first liquid hydrogen supply module or the second liquid hydrogen supply module fails, thereby improving the safety of the aircraft; at the same time, it realizes the utilization of waste heat of the first and second engines and uses the cooling capacity of liquid hydrogen to cool the first and second engines, reducing the cooling equipment, thereby reducing the weight of the aircraft and improving the energy utilization efficiency of the airborne liquid hydrogen storage and supply system. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the overall structure of the airborne liquid hydrogen storage and supply system according to Embodiment 1 of the present invention;

[0028] Figure 2 This is a schematic diagram of the overall structure of the airborne liquid hydrogen storage and supply system of Embodiment 2 of the present invention;

[0029] Figure 3 This is a schematic diagram of the overall structure of the airborne liquid hydrogen storage and supply system of Embodiment 3 of the present invention.

[0030] Explanation of reference numerals in the attached figures:

[0031] 11. First liquid hydrogen storage tank; 12. First liquid hydrogen pipeline; 13. First liquid hydrogen storage tank outlet valve; 14. Second liquid hydrogen pipeline; 15. First liquid hydrogen pump inlet control valve; 16. First liquid hydrogen pump; 17. Second liquid hydrogen pump inlet control valve; 18. Second liquid hydrogen pump; 19. Third liquid hydrogen pipeline; 21. Second liquid hydrogen storage tank; 22. Fourth liquid hydrogen pipeline; 23. Second liquid hydrogen storage tank outlet valve; 24. Fifth liquid hydrogen pipeline; 25. Third liquid hydrogen pump inlet control valve; 26. Third liquid hydrogen pump; 27. Fourth liquid hydrogen pump inlet control valve 28. Control valve; 29. ​​Fourth liquid hydrogen pump; 30. Sixth liquid hydrogen pipeline; 31. First heater; 32. First gaseous hydrogen pipeline; 33. First liquid hydrogen reheating gas supply pipeline; 34. First heat exchanger; 35. First heat pipe; 36. First centrifugal pump; 41. Second heater; 42. Second gaseous hydrogen pipeline; 43. Second liquid hydrogen reheating gas supply pipeline; 44. Second heat exchanger; 45. Second heat pipe; 46. Second centrifugal pump; 51. First control valve; 52. Second control valve; 61. First engine; 62. Second engine. Detailed Implementation

[0032] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0033] like Figures 1 to 3 As shown, the present invention provides an airborne liquid hydrogen storage and supply system, comprising:

[0034] The first liquid hydrogen storage and supply module includes: a first liquid hydrogen supply module and a first gaseous hydrogen supply module, which are connected to each other. The first liquid hydrogen supply module includes: a first liquid hydrogen storage tank 11, a first liquid hydrogen pipeline 12, a first liquid hydrogen storage tank outlet valve 13, a second liquid hydrogen pipeline 14, a first power pump module, and a third liquid hydrogen pipeline 19. The outlet of the first liquid hydrogen storage tank 11 is connected to the first end of the first liquid hydrogen pipeline 12, the second end of the first liquid hydrogen pipeline 12 is connected to the inlet of the first liquid hydrogen storage tank outlet valve 13, one end of the second liquid hydrogen pipeline 14 is connected to the outlet of the first liquid hydrogen storage tank outlet valve 13, the other end of the second liquid hydrogen pipeline 14 is connected to the inlet of the first power pump module, the outlet of the first power pump module is connected to one end of the third liquid hydrogen pipeline 19, and the other end of the third liquid hydrogen pipeline 19 is connected to the first gaseous hydrogen supply module. The first gaseous hydrogen supply module is used to heat liquid hydrogen to vaporize it into hydrogen gas to supply the first engine 61 of the aircraft.

[0035] The second liquid hydrogen storage and supply module includes a second liquid hydrogen supply module and a second gaseous hydrogen supply module, which are connected to each other. The second liquid hydrogen supply module includes a second liquid hydrogen storage tank 21, a fourth liquid hydrogen pipeline 22, a second liquid hydrogen storage tank outlet valve 23, a fifth liquid hydrogen pipeline 24, and a sixth liquid hydrogen pipeline 29. The outlet of the second liquid hydrogen storage tank 21 is connected to the first end of the fourth liquid hydrogen pipeline 22, the second end of the fourth liquid hydrogen pipeline 22 is connected to the inlet of the second liquid hydrogen storage tank outlet valve 23, one end of the fifth liquid hydrogen pipeline 24 is connected to the outlet of the second liquid hydrogen storage tank outlet valve 23, the other end of the fifth liquid hydrogen pipeline 24 is connected to the inlet of the second power pump module, the outlet of the second power pump module is connected to one end of the sixth liquid hydrogen pipeline 29, and the other end of the sixth liquid hydrogen pipeline 29 is connected to the second gaseous hydrogen supply module. The second gaseous hydrogen supply module is used to heat liquid hydrogen to vaporize it into hydrogen gas to supply the second engine 62 of the aircraft.

[0036] The first control valve 51 is located between the third liquid hydrogen pipeline 19 and the sixth liquid hydrogen pipeline 29, and is used to control the connection between the third liquid hydrogen pipeline 19 and the sixth liquid hydrogen pipeline 29.

[0037] The second control valve 52 is located between the first liquid hydrogen pipeline 12 and the fourth liquid hydrogen pipeline 22, and is used to control the connection between the first liquid hydrogen pipeline 12 and the fourth liquid hydrogen pipeline 22.

[0038] Under normal operating conditions of the airborne liquid hydrogen storage and supply system, the first control valve 51 and the second control valve 52 are closed. Liquid hydrogen is supplied from the first liquid hydrogen supply module to the first gaseous hydrogen supply module. The first gaseous hydrogen supply module heats the liquid hydrogen to vaporize it into hydrogen gas, which is then supplied to the aircraft's first engine 61. The first gaseous hydrogen supply module recovers the waste heat from the first engine 61 to heat and vaporize the liquid hydrogen, and uses the cooling capacity of the liquid hydrogen to cool the first engine 61. Therefore, no additional cooling equipment is required to cool the first engine 61. Liquid hydrogen is supplied from the second liquid hydrogen supply module to the second gaseous hydrogen supply module. The second gaseous hydrogen supply module heats the liquid hydrogen to vaporize it into hydrogen gas, which is then supplied to the aircraft's second engine 62. The second gaseous hydrogen supply module recovers the waste heat from the second engine 62 to heat and vaporize the liquid hydrogen, and uses the cooling capacity of the liquid hydrogen to cool the second engine 62. Therefore, no additional cooling equipment is required to cool the second engine 62.

[0039] When the first power pump module of the first liquid hydrogen supply module malfunctions, the first control valve 51 opens, thereby connecting the second liquid hydrogen supply module with the first gaseous hydrogen supply module through the first control valve 51. The second liquid hydrogen supply module supplies liquid hydrogen to both the first and second gaseous hydrogen supply modules. The first and second gaseous hydrogen supply modules heat the liquid hydrogen to vaporize it into hydrogen gas, which is then supplied to the first engine 61 and the second engine 62 of the aircraft, respectively. Similarly, when the second power pump module of the second liquid hydrogen supply module malfunctions, the first control valve 51 opens, thereby connecting the first liquid hydrogen supply module with the second gaseous hydrogen supply module through the first control valve 51. The first liquid hydrogen supply module supplies liquid hydrogen to both the first and second gaseous hydrogen supply modules. The first and second gaseous hydrogen supply modules heat the liquid hydrogen to vaporize it into hydrogen gas, which is then supplied to the first engine 61 and the second engine 62 of the aircraft, respectively.

[0040] When the first liquid hydrogen storage tank 11 malfunctions, the outlet valve 13 of the first liquid hydrogen storage tank is closed, and the second control valve 52 is opened, so that the first power pump module draws liquid hydrogen from the second liquid hydrogen storage tank 21 to supply the first gaseous hydrogen supply module; similarly, when the second liquid hydrogen storage tank 21 malfunctions, the outlet valve 23 of the second liquid hydrogen storage tank is closed, and the second control valve 52 is opened, so that the second power pump module draws liquid hydrogen from the second liquid hydrogen storage tank 21 to supply the second gaseous hydrogen supply module.

[0041] Therefore, the airborne liquid hydrogen storage and supply system of the present invention can still guarantee the supply of hydrogen to the first engine 61 and the second engine 62 of the aircraft even when the first liquid hydrogen supply module or the second liquid hydrogen supply module fails, thereby improving the safety of the aircraft. Simultaneously, it enables the utilization of waste heat from the first engine 61 and the second engine 62, and uses the cooling capacity of liquid hydrogen to cool the first engine 61 and the second engine 62, reducing the need for cooling equipment, thereby reducing the weight of the aircraft and improving the energy efficiency of the airborne liquid hydrogen storage and supply system.

[0042] When the first liquid hydrogen pump 16 of the first liquid hydrogen supply module malfunctions, the first liquid hydrogen pump inlet control valve 15 is closed, and the second liquid hydrogen pump inlet control valve 17 is opened, allowing the second liquid hydrogen pump 18 to supply liquid hydrogen to the first gaseous hydrogen supply module. Similarly, when the second liquid hydrogen pump 18 of the first liquid hydrogen supply module malfunctions, the second liquid hydrogen pump inlet control valve 17 is closed, and the first liquid hydrogen pump inlet control valve 15 is opened, allowing the first liquid hydrogen pump 16 to supply liquid hydrogen to the first gaseous hydrogen supply module. When the third liquid hydrogen pump 26 of the second liquid hydrogen supply module malfunctions, the third liquid hydrogen pump inlet control valve 25 is closed, and the fourth liquid hydrogen pump inlet control valve 27 is opened, allowing the fourth liquid hydrogen pump 28 to supply liquid hydrogen to the second gaseous hydrogen supply module. Similarly, when the fourth liquid hydrogen pump 28 of the second liquid hydrogen supply module malfunctions, the fourth liquid hydrogen pump inlet control valve 27 is closed, and the third liquid hydrogen pump inlet control valve 25 is opened, allowing the third liquid hydrogen pump 26 to supply liquid hydrogen to the second gaseous hydrogen supply module.

[0043] Furthermore, in order to ensure that the liquid hydrogen in the first liquid hydrogen storage tank 11 can smoothly reach the first gaseous hydrogen supply module or the second gaseous hydrogen supply module, the first power pump module includes: a first liquid hydrogen pump inlet control valve 15, a first liquid hydrogen pump 16, a second liquid hydrogen pump inlet control valve 17, and a second liquid hydrogen pump 18; the first end of the second liquid hydrogen pipeline 14 is connected to the outlet of the first liquid hydrogen storage tank outlet valve 13, the second end of the second liquid hydrogen pipeline 14 is connected to the first liquid hydrogen pump 16 through the first liquid hydrogen pump inlet control valve 15, the third end of the second liquid hydrogen pipeline 14 is connected to the second liquid hydrogen pump 18 through the second liquid hydrogen pump inlet control valve 17, the first liquid hydrogen pump 16 is connected to the first end of the third liquid hydrogen pipeline 19, the second liquid hydrogen pump 18 is connected to the second end of the third liquid hydrogen pipeline 19, and the third end of the third liquid hydrogen pipeline 19 is connected to the first gaseous hydrogen supply module.

[0044] The first liquid hydrogen supply module is equipped with a first liquid hydrogen pump 16 and a second liquid hydrogen pump 18. During normal operation, the first liquid hydrogen supply module can be powered by the first liquid hydrogen pump 16 or the second liquid hydrogen pump 18 to drive liquid hydrogen to flow to the first gaseous hydrogen supply module.

[0045] When powered by the first liquid hydrogen pump 16, the outlet valve 13 of the first liquid hydrogen storage tank is open, the inlet control valve 15 of the first liquid hydrogen pump is open, and the inlet control valve 17 of the second liquid hydrogen pump is closed. Driven by the power of the first liquid hydrogen pump 16, liquid hydrogen flows through the first liquid hydrogen pipeline 12, the outlet valve 13 of the first liquid hydrogen storage tank, the second liquid hydrogen pipeline 14, the inlet control valve 15 of the first liquid hydrogen pump, the first liquid hydrogen pump 16, and the third liquid hydrogen pipeline 19, and enters the first gaseous hydrogen supply module from the third liquid hydrogen pipeline 19. If the first control valve 51 is open, the liquid hydrogen in the third liquid hydrogen pipeline 19 can also enter the sixth liquid hydrogen pipeline 29.

[0046] When powered by the first liquid hydrogen pump 16, the outlet valve 13 of the first liquid hydrogen storage tank is open, the inlet control valve 17 of the second liquid hydrogen pump is open, and the inlet control valve 15 of the first liquid hydrogen pump is closed. Driven by the power of the second liquid hydrogen pump 18, liquid hydrogen flows through the first liquid hydrogen pipeline 12, the outlet valve 13 of the first liquid hydrogen storage tank, the second liquid hydrogen pipeline 14, the inlet control valve 17 of the second liquid hydrogen pump, the second liquid hydrogen pump 18, and the third liquid hydrogen pipeline 19, and enters the first gaseous hydrogen supply module from the third liquid hydrogen pipeline 19. If the first control valve 51 is open, the liquid hydrogen in the third liquid hydrogen pipeline 19 can also enter the sixth liquid hydrogen pipeline 29.

[0047] If a malfunction occurs while the first liquid hydrogen pump 16 is providing power, the second liquid hydrogen pump inlet control valve 17 will be opened and the first liquid hydrogen pump inlet control valve 15 will be closed, with the second liquid hydrogen pump 18 providing power; if a malfunction occurs while the second liquid hydrogen pump 18 is providing power, the first liquid hydrogen pump inlet control valve 15 will be opened and the second liquid hydrogen pump inlet control valve 17 will be closed, with the first liquid hydrogen pump 16 providing power.

[0048] Furthermore, to ensure that the liquid hydrogen in the second liquid hydrogen storage tank 21 can smoothly reach the second gaseous hydrogen supply module or the first gaseous hydrogen supply module, the second power pump module includes: a third liquid hydrogen pump inlet control valve 25, a third liquid hydrogen pump 26, a fourth liquid hydrogen pump inlet control valve 27, and a fourth liquid hydrogen pump 28; the first end of the fifth liquid hydrogen pipeline 24 is connected to the outlet of the second liquid hydrogen storage tank outlet valve 23, the second end of the fifth liquid hydrogen pipeline 24 is connected to the third liquid hydrogen pump 26 through the third liquid hydrogen pump inlet control valve 25, the third end of the fifth liquid hydrogen pipeline 24 is connected to the fourth liquid hydrogen pump 28 through the fourth liquid hydrogen pump inlet control valve 27, the third liquid hydrogen pump 26 is connected to the first end of the sixth liquid hydrogen pipeline 29, the fourth liquid hydrogen pump 28 is connected to the second end of the sixth liquid hydrogen pipeline 29, and the third end of the sixth liquid hydrogen pipeline 29 is connected to the second gaseous hydrogen supply module.

[0049] The second liquid hydrogen supply module is equipped with a third liquid hydrogen pump 26 and a fourth liquid hydrogen pump 28. During normal operation, the second liquid hydrogen supply module can be powered by the third liquid hydrogen pump 26 or the fourth liquid hydrogen pump 28 to drive liquid hydrogen to the second gaseous hydrogen supply module.

[0050] When powered by the third liquid hydrogen pump 26, the outlet valve 23 of the second liquid hydrogen storage tank is opened, the inlet control valve 25 of the third liquid hydrogen pump is opened, and the inlet control valve 27 of the fourth liquid hydrogen pump is closed. Under the power of the third liquid hydrogen pump 26, liquid hydrogen flows through the fourth liquid hydrogen pipeline 22, the outlet valve 23 of the second liquid hydrogen storage tank, the fifth liquid hydrogen pipeline 24, the inlet control valve 25 of the third liquid hydrogen pump, the third liquid hydrogen pump 26, and the sixth liquid hydrogen pipeline 29. It enters the first gaseous hydrogen supply module from the sixth liquid hydrogen pipeline 29. If the first control valve 51 is opened, the liquid hydrogen in the sixth liquid hydrogen pipeline 29 can also enter the third liquid hydrogen pipeline 19.

[0051] When powered by the fourth liquid hydrogen pump 28, the outlet valve 23 of the second liquid hydrogen storage tank opens, the inlet control valve 27 of the fourth liquid hydrogen pump opens, and the inlet control valve 25 of the third liquid hydrogen pump closes. Driven by the power of the fourth liquid hydrogen pump 28, liquid hydrogen flows through the fourth liquid hydrogen pipeline 22, the outlet valve 23 of the second liquid hydrogen storage tank, the fifth liquid hydrogen pipeline 24, the inlet control valve 27 of the fourth liquid hydrogen pump, the fourth liquid hydrogen pump 28, and the sixth liquid hydrogen pipeline 29. It enters the first gaseous hydrogen supply module from the sixth liquid hydrogen pipeline 29. If the first control valve 51 is opened, the liquid hydrogen in the sixth liquid hydrogen pipeline 29 can also enter the third liquid hydrogen pipeline 19.

[0052] If a malfunction occurs while the third liquid hydrogen pump 26 is providing power, the fourth liquid hydrogen pump inlet control valve 27 will be opened and the third liquid hydrogen pump inlet control valve 25 will be closed, with the fourth liquid hydrogen pump 28 providing power; if a malfunction occurs while the fourth liquid hydrogen pump 28 is providing power, the third liquid hydrogen pump inlet control valve 25 will be opened and the fourth liquid hydrogen pump inlet control valve 27 will be closed, with the third liquid hydrogen pump 26 providing power.

[0053] With the above configuration, the first liquid hydrogen supply module can supply liquid hydrogen to the first gaseous hydrogen supply module using the second liquid hydrogen pump 18 when the first liquid hydrogen pump 16 fails, and vice versa, thereby improving the stability of the first liquid hydrogen supply module. Similarly, the second liquid hydrogen supply module can supply liquid hydrogen to the second gaseous hydrogen supply module using the fourth liquid hydrogen pump 28 when the third liquid hydrogen pump 26 fails, and vice versa, thereby improving the stability of the second liquid hydrogen supply module.

[0054] When both the first liquid hydrogen pump 16 and the second liquid hydrogen pump 18 fail simultaneously, the first control valve 51 opens, allowing liquid hydrogen from the third liquid hydrogen line 19 to still flow into the sixth liquid hydrogen line 29 and supply liquid hydrogen to the second gaseous hydrogen supply module. Similarly, when both the third liquid hydrogen pump 26 and the fourth liquid hydrogen pump 28 fail simultaneously, the first control valve 51 opens, allowing liquid hydrogen from the sixth liquid hydrogen line 29 to still flow into the third liquid hydrogen line 19 and supply liquid hydrogen to the first gaseous hydrogen supply module.

[0055] The first liquid hydrogen storage tank 11 and the second liquid hydrogen storage tank 21 can be vacuum multi-layer insulation liquid hydrogen storage tanks or liquid hydrogen storage tanks with other insulation methods, as long as they meet the usage requirements. The tank body material can be stainless steel, aluminum alloy, titanium alloy or composite material.

[0056] The first liquid hydrogen pipeline 12, the second liquid hydrogen pipeline 14, the third liquid hydrogen pipeline 19, the fourth liquid hydrogen pipeline 22, the fifth liquid hydrogen pipeline 24, and the sixth liquid hydrogen pipeline 29 are cryogenic transmission pipelines with a vacuum multi-layer insulation structure. They can also be cryogenic transmission pipelines with other insulation methods, as long as they meet the usage requirements. The pipeline body material can be stainless steel, aluminum alloy, titanium alloy, or composite material. They can be rigid pipes or flexible pipes, and cryogenic joints can be installed in the middle as needed.

[0057] Under normal conditions, the second control valve 52 is closed when the first liquid hydrogen storage tank 11 and the second liquid hydrogen storage tank 21 are in normal operation.

[0058] When the first liquid hydrogen storage tank 11 malfunctions, the second control valve 52 can be opened, which allows the first liquid hydrogen pump 16 or the second liquid hydrogen pump 18 to drive the liquid hydrogen from the second liquid hydrogen storage tank 21 to the first gaseous hydrogen supply module, thereby filling the gap in the supply of liquid hydrogen to the first gaseous hydrogen supply module due to the failure of the first liquid hydrogen storage tank 11.

[0059] Similarly, when the second liquid hydrogen storage tank 21 malfunctions, the second control valve 52 can be opened, which allows the third liquid hydrogen pump 26 or the fourth liquid hydrogen pump 28 to drive the liquid hydrogen from the first liquid hydrogen storage tank 11 to the second gaseous hydrogen supply module, thereby filling the gap in the supply of liquid hydrogen to the second gaseous hydrogen supply module due to the malfunction of the second liquid hydrogen storage tank 21.

[0060] Furthermore, the first liquid hydrogen pump 16, the second liquid hydrogen pump 18, the third liquid hydrogen pump 26 and the fourth liquid hydrogen pump 28 are centrifugal or plunger type liquid hydrogen pumps to meet the requirements of pressurization and flow. When the inlet and outlet are connected to the cryogenic pipeline, a special cryogenic connector is used to prevent excessive heat leakage from causing equipment icing or freezing damage to the sealing structure.

[0061] The first liquid hydrogen storage tank outlet valve 13, the first liquid hydrogen pump inlet control valve 15, the second liquid hydrogen pump inlet control valve 17, the second liquid hydrogen storage tank outlet valve 23, the third liquid hydrogen pump inlet control valve 25, the fourth liquid hydrogen pump inlet control valve 27, the first control valve 51, and the second control valve 52 are all cryogenic valves applied to the temperature of liquid hydrogen. They can be pneumatically or electrically operated and meet the requirements for the use of liquid hydrogen.

[0062] like Figure 1 As shown, in one embodiment of the present invention, the first gaseous hydrogen supply module includes: a first heater 31, a first gaseous hydrogen pipeline 32 and a first liquid hydrogen reheating gas supply pipeline 33. The inlet of the first heater 31 is connected to the first liquid hydrogen supply module, the outlet of the first heater 31 is connected to the first end of the first gaseous hydrogen pipeline 32, the second end of the first gaseous hydrogen pipeline 32 is connected to the inlet of the cooling channel of the first engine 61, the outlet of the cooling channel of the first engine 61 is connected to the first end of the first liquid hydrogen reheating gas supply pipeline 33, and the second end of the first liquid hydrogen reheating gas supply pipeline 33 is connected to the feed port of the first engine 61.

[0063] The second gaseous hydrogen supply module includes: a second heater 41, a second gaseous hydrogen pipeline 42, and a second liquid hydrogen reheating supply pipeline 43. The inlet of the second heater 41 is connected to the second liquid hydrogen supply module, the outlet of the second heater 41 is connected to the first end of the second gaseous hydrogen pipeline 42, the second end of the second gaseous hydrogen pipeline 42 is connected to the inlet of the cooling channel of the second engine 62, the outlet of the cooling channel of the second engine 62 is connected to the first end of the first liquid hydrogen reheating supply pipeline 33, and the second end of the first liquid hydrogen reheating supply pipeline 33 is connected to the feed port of the second engine 62.

[0064] During the startup phase of the airborne liquid hydrogen storage and supply system, the first engine 61 and the second engine 62 are not in operation, and the heat for liquid hydrogen vaporization is mainly provided by the first heater 31 and the second heater 41.

[0065] During the stable operation phase of the airborne liquid hydrogen storage and supply system, the first heater 31 and the second heater 41 are shut down. Liquid hydrogen enters the cooling channels of the first engine 61 and the second engine 62, absorbing heat from them and cooling them. Simultaneously, the heat for liquid hydrogen vaporization is primarily provided by the first engine 61 and the second engine 62. After vaporization, the liquid hydrogen enters the first engine 61 and the second engine 62 for combustion via the first liquid hydrogen reheat supply line 33 and the second liquid hydrogen reheat supply line 43, respectively. This reduces the need for refrigeration equipment in traditional engine cooling systems, lowers aircraft weight, and improves energy efficiency.

[0066] like Figure 2 As shown, in another embodiment of the present invention, the first gaseous hydrogen supply module includes: a first heat exchanger 34, a first heater 31, a first gaseous hydrogen pipeline 32 and a first heat pipe 35. The cold inlet of the first heat exchanger 34 is connected to the first liquid hydrogen supply module, the hot inlet of the first heat exchanger 34 is connected to the outlet of the first heat pipe 35, the inlet of the first heat pipe 35 is connected to the first engine 61, the outlet of the first heat exchanger 34 is connected to the inlet of the first heater 31, the outlet of the first heater 31 is connected to the first end of the first gaseous hydrogen pipeline 32, and the second end of the first gaseous hydrogen pipeline 32 is connected to the feed port of the first engine 61.

[0067] The second gaseous hydrogen supply module includes: a second heat exchanger 44, a second heater 41, a second gaseous hydrogen pipeline 42, and a second heat pipe 45. The cold inlet of the second heat exchanger 44 is connected to the second liquid hydrogen supply module, the hot inlet of the second heat exchanger 44 is connected to the outlet of the second heat pipe 45, the inlet of the second heat pipe 45 is connected to the second engine 62, the outlet of the second heat exchanger 44 is connected to the inlet of the second heater 41, the outlet of the second heater 41 is connected to the first end of the second gaseous hydrogen pipeline 42, and the second end of the second gaseous hydrogen pipeline 42 is connected to the feed port of the second engine 62.

[0068] During the startup phase of the airborne liquid hydrogen storage and supply system, the first engine 61 and the second engine 62 are not in operation, and the heat for liquid hydrogen vaporization is mainly provided by the first heater 31 and the second heater 41.

[0069] During the stable operation phase of the airborne liquid hydrogen storage and supply system, the first heater 31 and the second heater 41 are shut down. Liquid hydrogen enters the cold passages of the first heat exchanger 34 and the second heat exchanger 44, while the cooling medium for the first engine 61 and the second engine 62 enters the hot passages of the first heat exchanger 34 and the second heat exchanger 44 through the first heat pipe 35 and the second heat pipe 45, respectively. Heat exchange occurs between the first heat exchanger 34 and the second heat exchanger 44, cooling the first engine 61 and the second engine 62. Simultaneously, the heat for liquid hydrogen vaporization is primarily provided by the first engine 61 and the second engine 62. After vaporization, the liquid hydrogen enters the first engine 61 and the second engine 62 for combustion through the first gaseous hydrogen pipeline 32 and the second gaseous hydrogen pipeline 42, respectively. This reduces the amount of refrigeration equipment in the traditional engine cooling system, lowers the aircraft weight, and improves energy efficiency.

[0070] like Figure 3 As shown, in another embodiment of the present invention, the first gaseous hydrogen supply module includes: a first heat exchanger 34, a first heater 31, a first centrifugal pump 36, a first gaseous hydrogen pipeline 32 and a first heat pipe 35. The cold inlet of the first heat exchanger 34 is connected to the first liquid hydrogen supply module, the hot inlet of the first heat exchanger 34 is connected to the outlet of the first heat pipe 35, the inlet of the first heat pipe 35 is connected to the first engine 61, the outlet of the first heat exchanger 34 is connected to the inlet of the first centrifugal pump 36, the outlet of the first centrifugal pump 36 is connected to the inlet of the first heater 31, the outlet of the first heater 31 is connected to the first end of the first gaseous hydrogen pipeline 32, and the second end of the first gaseous hydrogen pipeline 32 is connected to the feed port of the first engine 61.

[0071] The second gaseous hydrogen supply module includes: a second heat exchanger 44, a second heater 41, a second centrifugal pump 46, a second gaseous hydrogen pipeline 42, and a second heat pipe 45. The cold inlet of the second heat exchanger 44 is connected to the second liquid hydrogen supply module, the hot inlet of the second heat exchanger 44 is connected to the outlet of the second heat pipe 45, the inlet of the second heat pipe 45 is connected to the second engine 62, the outlet of the second heat exchanger 44 is connected to the inlet of the second centrifugal pump 46, the outlet of the second centrifugal pump 46 is connected to the inlet of the second heater 41, the outlet of the second heater 41 is connected to the first end of the second gaseous hydrogen pipeline 42, and the second end of the second gaseous hydrogen pipeline 42 is connected to the feed port of the second engine 62.

[0072] During the startup phase of the airborne liquid hydrogen storage and supply system, the first engine 61 and the second engine 62 are not in operation, and the heat for liquid hydrogen vaporization is mainly provided by the first heater 31 and the second heater 41.

[0073] During the stable operation phase of the airborne liquid hydrogen storage and supply system, the first heater 31 and the second heater 41 are shut down. Liquid hydrogen enters the cold passages of the first heat exchanger 34 and the second heat exchanger 44, while the cooling medium for the first engine 61 and the second engine 62 enters the hot passages of the first heat exchanger 34 and the second heat exchanger 44 through the first heat pipe 35 and the second heat pipe 45, respectively. Heat exchange occurs between the first heat exchanger 34 and the second heat exchanger 44, cooling the first engine 61 and the second engine 62. Simultaneously, the heat for liquid hydrogen vaporization is primarily provided by the first engine 61 and the second engine 62. After vaporization, the liquid hydrogen is pumped into the first engine 61 and the second engine 62 through the first gaseous hydrogen pipeline 32 and the second gaseous hydrogen pipeline 42 via the first centrifugal pump 36 and the second centrifugal pump 46, respectively, for combustion. This reduces the amount of refrigeration equipment in the traditional engine cooling system, lowers the aircraft weight, and improves energy efficiency.

[0074] Furthermore, the first heat exchanger 34 and the second heat exchanger 44 are aluminum plate heat exchangers or plate-fin heat exchangers.

[0075] The above description is merely a preferred embodiment of the present invention and does not constitute any limitation on the technical scope of the present invention. Therefore, any minor modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention shall still fall within the scope of the technical solution of the present invention.

Claims

1. An airborne liquid hydrogen storage and supply system, characterized in that, include: A first liquid hydrogen storage and supply module includes a first liquid hydrogen supply module and a first gaseous hydrogen supply module. The first liquid hydrogen supply module includes a first liquid hydrogen storage tank, a first liquid hydrogen pipeline, a first liquid hydrogen storage tank outlet valve, a second liquid hydrogen pipeline, a first power pump module, and a third liquid hydrogen pipeline. The outlet of the first liquid hydrogen storage tank is connected to a first end of the first liquid hydrogen pipeline, the second end of the first liquid hydrogen pipeline is connected to the inlet of the first liquid hydrogen storage tank outlet valve, one end of the second liquid hydrogen pipeline is connected to the outlet of the first liquid hydrogen storage tank outlet valve, the other end of the second liquid hydrogen pipeline is connected to the inlet of the first power pump module, the outlet of the first power pump module is connected to the inlet of the third liquid hydrogen pipeline, and the outlet of the third liquid hydrogen pipeline is connected to the first gaseous hydrogen supply module. The first gaseous hydrogen supply module is used to heat liquid hydrogen to vaporize it into hydrogen gas to supply the first engine of the aircraft. The second liquid hydrogen storage and supply module includes a second liquid hydrogen supply module and a second gaseous hydrogen supply module. The second liquid hydrogen supply module includes a second liquid hydrogen storage tank, a fourth liquid hydrogen pipeline, a second liquid hydrogen storage tank outlet valve, a fifth liquid hydrogen pipeline, a second power pump module, and a sixth liquid hydrogen pipeline. The outlet of the second liquid hydrogen storage tank is connected to the first end of the fourth liquid hydrogen pipeline, the second end of the fourth liquid hydrogen pipeline is connected to the inlet of the second liquid hydrogen storage tank outlet valve, one end of the fifth liquid hydrogen pipeline is connected to the outlet of the second liquid hydrogen storage tank outlet valve, the other end of the fifth liquid hydrogen pipeline is connected to the inlet of the second power pump module, the outlet of the second power pump module is connected to the inlet of the sixth liquid hydrogen pipeline, and the outlet of the sixth liquid hydrogen pipeline is connected to the second gaseous hydrogen supply module. The second gaseous hydrogen supply module is used to heat liquid hydrogen to vaporize it into hydrogen gas to supply the second engine of the aircraft. A first control valve is disposed between the third liquid hydrogen pipeline and the sixth liquid hydrogen pipeline, and is used to control the connection between the third liquid hydrogen pipeline and the sixth liquid hydrogen pipeline; A second control valve is disposed between the first liquid hydrogen pipeline and the fourth liquid hydrogen pipeline, and is used to control the connection between the first liquid hydrogen pipeline and the fourth liquid hydrogen pipeline.

2. The airborne liquid hydrogen storage and supply system according to claim 1, characterized in that, The first power pump module includes: a first liquid hydrogen pump inlet control valve, a first liquid hydrogen pump, a second liquid hydrogen pump inlet control valve, and a second liquid hydrogen pump; the first end of the second liquid hydrogen pipeline is connected to the outlet of the first liquid hydrogen storage tank outlet valve, the second end of the second liquid hydrogen pipeline is connected to the first liquid hydrogen pump through the first liquid hydrogen pump inlet control valve, the third end of the second liquid hydrogen pipeline is connected to the second liquid hydrogen pump through the second liquid hydrogen pump inlet control valve, the first liquid hydrogen pump is connected to the first end of the third liquid hydrogen pipeline, the second liquid hydrogen pump is connected to the second end of the third liquid hydrogen pipeline, and the third end of the third liquid hydrogen pipeline is connected to the first gaseous hydrogen supply module.

3. The airborne liquid hydrogen storage and supply system according to claim 2, characterized in that, The first liquid hydrogen pump and the second liquid hydrogen pump are centrifugal or plunger type liquid hydrogen pumps.

4. The airborne liquid hydrogen storage and supply system according to claim 1, characterized in that, The second power pump module includes: a third liquid hydrogen pump inlet control valve, a third liquid hydrogen pump, a fourth liquid hydrogen pump inlet control valve, and a fourth liquid hydrogen pump; the first end of the fifth liquid hydrogen pipeline is connected to the outlet of the second liquid hydrogen storage tank outlet valve, the second end of the fifth liquid hydrogen pipeline is connected to the third liquid hydrogen pump through the third liquid hydrogen pump inlet control valve, the third end of the fifth liquid hydrogen pipeline is connected to the fourth liquid hydrogen pump through the fourth liquid hydrogen pump inlet control valve, the third liquid hydrogen pump is connected to the first end of the sixth liquid hydrogen pipeline, the fourth liquid hydrogen pump is connected to the second end of the sixth liquid hydrogen pipeline, and the third end of the sixth liquid hydrogen pipeline is connected to the second gaseous hydrogen supply module.

5. The airborne liquid hydrogen storage and supply system according to claim 4, characterized in that, The third liquid hydrogen pump and the fourth liquid hydrogen pump are centrifugal or plunger type liquid hydrogen pumps.

6. The airborne liquid hydrogen storage and supply system according to claim 1, characterized in that, The first gaseous hydrogen supply module includes: a first heater, a first gaseous hydrogen pipeline and a first liquid hydrogen reheating gas supply pipeline. The inlet of the first heater is connected to the first liquid hydrogen supply module, the outlet of the first heater is connected to the first end of the first gaseous hydrogen pipeline, the second end of the first gaseous hydrogen pipeline is connected to the inlet of the cooling channel of the first engine, the outlet of the cooling channel of the first engine is connected to the first end of the first liquid hydrogen reheating gas supply pipeline, and the second end of the first liquid hydrogen reheating gas supply pipeline is connected to the feed port of the first engine. The second gaseous hydrogen supply module includes: a second heater, a second gaseous hydrogen pipeline, and a second liquid hydrogen reheating supply pipeline. The inlet of the second heater is connected to the second liquid hydrogen supply module, the outlet of the second heater is connected to the first end of the second gaseous hydrogen pipeline, the second end of the second gaseous hydrogen pipeline is connected to the inlet of the cooling channel of the second engine, the outlet of the cooling channel of the second engine is connected to the first end of the first liquid hydrogen reheating supply pipeline, and the second end of the first liquid hydrogen reheating supply pipeline is connected to the feed port of the second engine.

7. The airborne liquid hydrogen storage and supply system according to claim 1, characterized in that, The first gaseous hydrogen supply module includes: a first heat exchanger, a first heater, a first gaseous hydrogen pipeline and a first heat pipe. The cold inlet of the first heat exchanger is connected to the first liquid hydrogen supply module, the hot inlet of the first heat exchanger is connected to the outlet of the first heat pipe, the inlet of the first heat pipe is connected to the first engine, the outlet of the first heat exchanger is connected to the inlet of the first heater, the outlet of the first heater is connected to the first end of the first gaseous hydrogen pipeline, and the second end of the first gaseous hydrogen pipeline is connected to the feed port of the first engine. The second gaseous hydrogen supply module includes: a second heat exchanger, a second heater, a second gaseous hydrogen pipeline and a second heat pipe. The cold inlet of the second heat exchanger is connected to the second liquid hydrogen supply module, the hot inlet of the second heat exchanger is connected to the outlet of the second heat pipe, the inlet of the second heat pipe is connected to the second engine, the outlet of the second heat exchanger is connected to the inlet of the second heater, the outlet of the second heater is connected to the first end of the second gaseous hydrogen pipeline, and the second end of the second gaseous hydrogen pipeline is connected to the feed port of the second engine.

8. The airborne liquid hydrogen storage and supply system according to claim 1, characterized in that, The first gaseous hydrogen supply module includes: a first heat exchanger, a first heater, a first centrifugal pump, a first gaseous hydrogen pipeline and a first heat pipe. The cold inlet of the first heat exchanger is connected to the first liquid hydrogen supply module, the hot inlet of the first heat exchanger is connected to the outlet of the first heat pipe, the inlet of the first heat pipe is connected to the first engine, the outlet of the first heat exchanger is connected to the inlet of the first centrifugal pump, the outlet of the first centrifugal pump is connected to the inlet of the first heater, the outlet of the first heater is connected to the first end of the first gaseous hydrogen pipeline, and the second end of the first gaseous hydrogen pipeline is connected to the feed port of the first engine. The second gaseous hydrogen supply module includes: a second heat exchanger, a second heater, a second centrifugal pump, a second gaseous hydrogen pipeline, and a second heat pipe. The cold inlet of the second heat exchanger is connected to the second liquid hydrogen supply module, the hot inlet of the second heat exchanger is connected to the outlet of the second heat pipe, the inlet of the second heat pipe is connected to the second engine, the outlet of the second heat exchanger is connected to the inlet of the second centrifugal pump, the outlet of the second centrifugal pump is connected to the inlet of the second heater, the outlet of the second heater is connected to the first end of the second gaseous hydrogen pipeline, and the second end of the second gaseous hydrogen pipeline is connected to the feed port of the second engine.

9. The airborne liquid hydrogen storage and supply system according to claim 7 or 8, characterized in that, The first heat exchanger and the second heat exchanger are aluminum plate heat exchangers or plate-fin heat exchangers.

Images