A liquid hydrogen fuel storage and supply system suitable for use in a hybrid hydrogen powered aircraft

Abstract

The application provides a liquid hydrogen fuel storage and supply system suitable for a hybrid hydrogen-powered aircraft, which comprises an engine circulation unit, the engine circulation unit comprising a first liquid hydrogen storage tank, a first booster pump group, a first heat exchanger, a second heat exchanger, a compressor and a hydrogen fuel engine, liquid hydrogen in the first liquid hydrogen storage tank is pressurized by the first booster pump group, and then sequentially passes through the second heat exchange side of the first heat exchanger, the second heat exchange side of the second heat exchanger, the first heat exchange side of the first heat exchanger and the second heat exchanger, and is heated and gasified by waste gas heat exchange of the first heat exchange side of the second heat exchanger, and is compressed by the compressor or directly enters the hydrogen fuel engine, the application can open different numbers of the first booster pump according to the actual demand of the hydrogen fuel engine, and then select to pressurize hydrogen or directly deliver hydrogen to the hydrogen fuel engine, control hydrogen with different pressure and flow to enter the hydrogen fuel engine, and ensure sufficient combustion of hydrogen and improve hydrogen utilization.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of fuel storage and supply, and particularly relates to a liquid hydrogen fuel storage and supply system suitable for a hybrid hydrogen-powered aircraft. BACKGROUND

[0002] Hydrogen-powered aircraft has become an important direction for future development. Hydrogen fuel power mainly has two forms of hydrogen fuel cell and hydrogen fuel engine. The hydrogen fuel cell only emits water vapor, is environmentally friendly and efficient, but has relatively low energy density and limited output power. The hydrogen fuel engine has high combustion efficiency and can meet the demand for large thrust. Therefore, the combination of the two can maximize the efficiency of the aircraft at different stages.

[0003] The prior art such as CN118358761A discloses a main-tail propeller separation full-hydrogen hybrid power propulsion system suitable for a heavy long-range helicopter, which provides a hybrid hydrogen power scheme of using a hydrogen fuel cell to drive a tail propeller alone to reduce mechanical transmission mechanisms, and realizes the heat exchange of liquid hydrogen and the cooling of oil for cooling main propeller motors, tail propeller motors and hydrogen fuel cells, and simultaneously realizes the gasification of liquid hydrogen and the cooling of high-temperature equipment. However, the hybrid power system does not consider the problem that the hydrogen gas inlet conditions of the hydrogen fuel turbine engine and the hydrogen fuel cell are different. If the different inlet conditions of hydrogen gas in the hydrogen fuel engine and the hydrogen fuel cell are not correctly adjusted, part of the hydrogen gas entering the hydrogen fuel engine cannot be fully combusted, which reduces the combustion efficiency of hydrogen gas, or part of the hydrogen gas entering the hydrogen fuel cell cannot be effectively reacted, which reduces the efficiency of the hydrogen fuel cell. SUMMARY

[0004] In order to solve the problem that the combustion efficiency or the efficiency of the hydrogen fuel cell cannot be fully improved, the present application provides a liquid hydrogen fuel storage and supply system suitable for a hybrid hydrogen-powered aircraft.

[0005] The present application is realized by the following technical solutions:

[0006] The present application provides a liquid hydrogen fuel storage and supply system suitable for a hybrid hydrogen-powered aircraft, which comprises an engine circulation unit.

[0007] The engine circulation unit comprises a first liquid hydrogen storage tank, a first booster pump group, a first heat exchanger, a second heat exchanger, a compressor and a hydrogen fuel engine, wherein:

[0008] The first boost pump group includes at least one first boost pump; the first heat exchange side of the first heat exchanger and the first heat exchange side of the second heat exchanger are connected to the hydrogen fuel engine and are used to exchange heat with the exhaust gas of the hydrogen fuel engine. The first liquid hydrogen storage tank is connected to the first boost pump group, the second heat exchange side of the first heat exchanger and the second heat exchange side of the second heat exchanger in sequence. One outlet of the second heat exchange side of the second heat exchanger is connected to the compressor and the hydrogen fuel engine in sequence, and the other outlet is directly connected to the hydrogen fuel engine. The liquid hydrogen passes through the second heat exchange side of the first heat exchanger, the second heat exchange side of the second heat exchanger, and the exhaust gas of the first heat exchange side and the first heat exchange side of the second heat exchanger to heat up and gasify, and is compressed by the compressor or directly enters the hydrogen fuel engine.

[0009] Furthermore, it also includes a battery circulation unit, which includes a second liquid hydrogen storage tank, a second boost pump, a third heat exchanger and a hydrogen fuel cell, wherein:

[0010] The first heat exchange side of the third heat exchanger is used to exchange heat with the coolant of the hydrogen fuel cell. The second liquid hydrogen storage tank is connected to the second boost pump, the second heat exchange side of the third heat exchanger and the hydrogen fuel cell in sequence. The liquid hydrogen passes through the second heat exchange side of the third heat exchanger and exchanges heat with the coolant on the first heat exchange side of the third heat exchanger to absorb heat, heat up and vaporize, and then enters the hydrogen fuel cell.

[0011] Furthermore, the battery circulation unit also includes a coolant storage tank, a coolant pump, a coolant filter and a heat exchanger. The heat exchanger is used to absorb the waste heat of the hydrogen fuel cell through the coolant. The outlet of the heat exchanger is connected to the first heat exchange side of the third heat exchanger, the coolant storage tank, the coolant pump and the coolant filter in sequence, and is connected back to the inlet of the heat exchanger from the coolant filter.

[0012] Furthermore, a first electric heater and a second electric heater are respectively provided inside the first liquid hydrogen storage tank and the second liquid hydrogen storage tank.

[0013] Furthermore, it also includes a cross-transfer hydrogen supply valve, both ends of which are respectively connected to the area between the first liquid hydrogen storage tank and the first booster pump group and to the area between the second liquid hydrogen storage tank and the second booster pump.

[0014] Further, when the first boost pump group includes a plurality of first boost pumps, the first liquid hydrogen storage tank is respectively connected to each of the first boost pumps and the first liquid hydrogen storage tank is connected to the second heat exchange side of the first heat exchanger.

[0015] Further, a first stop valve is arranged on the inlet end of each first booster pump, and a fourth stop valve is arranged on the inlet end of the second booster pump.

[0016] Further, a first flow regulating valve is arranged on the inlet of the hydrogen fuel engine.

[0017] Further, a second stop valve is connected to the second heat exchange side outlet of the second heat exchanger at one end and to the inlet of the hydrogen fuel engine at the other end, and a third stop valve is arranged between the second heat exchange side outlet of the second heat exchanger and the compressor.

[0018] Further, a second flow regulating valve is arranged between the second heat exchange side outlet of the third heat exchanger and the hydrogen fuel cell, and a pressure regulating valve is arranged between the first heat exchange side outlet of the third heat exchanger and the coolant tank.

[0019] Advantages of the present application:

[0020] (1) The liquid hydrogen fuel storage and supply system suitable for a hybrid hydrogen-powered aircraft according to the present application can open different numbers of first booster pumps according to the actual demand of the hydrogen fuel engine, and then select to pressurize the hydrogen or directly deliver it to the hydrogen fuel engine, so as to control the hydrogen with different pressures and flow rates entering the hydrogen fuel engine, thereby ensuring sufficient combustion of the hydrogen and improving the utilization rate of the hydrogen.

[0021] (2) The liquid hydrogen fuel storage and supply system suitable for a hybrid hydrogen-powered aircraft according to the present application can realize alternating delivery between the first liquid hydrogen tank and the second liquid hydrogen tank through the interdelivery hydrogen supply valve, so that the two tanks can be used as backup for each other under normal supply conditions, and provide hydrogen fuel for the engine circulation unit or the battery circulation unit. When one of the liquid hydrogen tanks fails, the interdelivery hydrogen supply valve can be opened to provide liquid hydrogen from the other tank, further ensuring safety. Or when one of the engine or battery circulation units fails, the stop valve or liquid hydrogen delivery pipeline of the failed unit can be closed, and if the other normal working unit needs additional hydrogen fuel, the interdelivery hydrogen supply valve can be opened to deliver the liquid hydrogen in the liquid hydrogen tank of the failed unit to the normal working unit.

[0022] (3) The liquid hydrogen fuel storage and supply system suitable for a hybrid hydrogen-powered aircraft according to the present application uses two different units for hydrogen fuel cells and hydrogen fuel engines to provide different hydrogen conditions, which makes the system more flexible, reliable and safe, and also adjusts the hydrogen flow according to the flight stage to improve the efficiency of the aircraft.

[0023] (4) The application realizes the purposes of cooling liquid heat exchange and liquid hydrogen gasification through the cooling liquid and liquid hydrogen of hydrogen fuel cell, reduces the necessary equipment and its weight, and has significant meaning for increasing the mass hydrogen storage ratio of liquid hydrogen fuel storage and supply system. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 The structural diagram of the liquid hydrogen fuel storage and supply system suitable for the hybrid hydrogen-powered aircraft of the application;

[0025] In the figure: the first liquid hydrogen storage tank 1, the first electric heater 2, the first stop valve 3, the first booster pump 4, the first heat exchanger 5, the second heat exchanger 6, the second stop valve 7, the third stop valve 8, the compressor 9, the first flow regulating valve 10, the hydrogen fuel engine 11, the engine exhaust pipe 12, the second liquid hydrogen storage tank 13, the second electric heater 14, the hydrogen supply valve 15, the fourth stop valve 16, the second booster pump 17, the third heat exchanger 18, the second flow regulating valve 19, the hydrogen fuel cell 20, the heat exchanger 21, the pressure regulating valve 22, the cooling liquid storage tank 23, the cooling liquid pump 24, and the cooling liquid filter 25.

[0026] The implementation, functional features and advantages of the application will be further described with reference to the embodiments and the accompanying drawings. DETAILED DESCRIPTION

[0027] In order to more clearly and completely explain the technical solutions of the application, the application will be further described below with reference to the accompanying drawings.

[0028] Please refer to Figure 1 The application provides a liquid hydrogen fuel storage and supply system suitable for a hybrid hydrogen-powered aircraft, which comprises an engine circulation unit, and the engine circulation unit comprises a first liquid hydrogen storage tank 1, a first booster pump 4 group, a first heat exchanger 5, a second heat exchanger 6, a compressor 9 and a hydrogen fuel engine 11, wherein:

[0029] The first booster pump 4 group comprises at least one first booster pump 4; the first heat exchange side of the first heat exchanger 5 and the first heat exchange side of the second heat exchanger 6 are connected to the hydrogen fuel engine 11 and used for heat exchange with the exhaust gas of the hydrogen fuel engine 11; the first liquid hydrogen storage tank 1 is connected to the first booster pump group 4, the second heat exchange side of the first heat exchanger 5 and the second heat exchange side of the second heat exchanger 6 in sequence; one outlet of the second heat exchange side of the second heat exchanger 6 is connected to the compressor 9 and the hydrogen fuel engine 11 in sequence, and the other outlet is directly connected to the hydrogen fuel engine 11; the liquid hydrogen is heat-exchanged and gasified by the exhaust gas of the first heat exchange side of the first heat exchanger 5 and the first heat exchange side of the second heat exchanger 6, and is compressed by the compressor 9 or directly enters into the hydrogen fuel engine 11.

[0030] In the specific embodiment, the first heat exchanger 5 and the second heat exchanger 6 are heat exchangers located at the tail of the engine in a high-temperature area such as the exhaust pipe and the rear section of the turbine, the engine exhaust pipe 12 of the hydrogen fuel engine 11 is connected with the first heat exchanger 5 and the second heat exchanger 6, the liquid hydrogen is extracted from the first liquid hydrogen storage tank 1 and is pressurized by the first group of booster pumps 4 to overcome the pressure drop along the pipeline.

[0031] Since the hydrogen inlet temperature of the hydrogen fuel engine 11 is high, the liquid hydrogen is first preheated by the second heat exchange side of the first heat exchanger 5 to start gasification, and the hydrogen fuel engine 11 is cooled at the same time; then the hydrogen fuel is further heated in the second heat exchange side of the second heat exchanger 6 to completely gasify, and the temperature is precisely controlled in the second heat exchanger 6 to ensure that the hydrogen gas is at an appropriate temperature and a relatively stable state before flowing into the hydrogen fuel engine 11. When the flow demand of the hydrogen fuel engine 11 is large, then the first group of booster pumps 4 opens multiple first booster pumps 4, and the hydrogen gas is pressurized again by the compressor 9 after being heated by the first heat exchanger 5 and the second heat exchanger 6 and then enters the hydrogen fuel engine 11; when the flow demand of the hydrogen fuel engine 11 is small, then the first group of booster pumps 4 opens one first booster pump 4, and the hydrogen gas directly enters the hydrogen fuel engine 11 after being heated by the first heat exchanger 5 and the second heat exchanger 6. The hydrogen gas enters the hydrogen fuel engine 11 and burns, and the high-temperature and high-pressure gas produced in the turbine expands to produce mechanical energy, thereby driving the fan or propeller to provide aircraft thrust. The two ways of supplying hydrogen can ensure that the hydrogen is fully burned in the combustion chamber of the hydrogen fuel engine 11 and mixed with air, increase the gas density, and promote the combustion efficiency. The present application can select hydrogen with different pressures and flow rates according to the actual demand of the hydrogen fuel engine 11 to ensure full combustion of hydrogen and improve the utilization rate of hydrogen.

[0032] Further, it also includes a battery circulation unit, which includes a second liquid hydrogen storage tank 13, a second booster pump 17, a third heat exchanger 18 and a hydrogen fuel cell 20, wherein:

[0033] The first heat exchange side of the third heat exchanger 18 is used for heat exchange with the cooling liquid of the hydrogen fuel cell 20, the second liquid hydrogen storage tank 13 is connected with the second booster pump 17, the second heat exchange side of the third heat exchanger 18 and the hydrogen fuel cell 20 in sequence, the liquid hydrogen is heated and gasified by heat exchange between the second heat exchange side of the third heat exchanger 18 and the cooling liquid of the first heat exchange side of the third heat exchanger 18, and then enters the hydrogen fuel cell 20.

[0034] In the specific embodiment, the second booster pump 17 is used to overcome the pressure drop along the pipeline during the delivery process. The liquid hydrogen in the second liquid hydrogen storage tank 13 is pressurized by the second booster pump 17, then warmed and gasified into hydrogen gas at the second heat exchange side of the third heat exchanger 18, and then enters the hydrogen fuel cell 20 to participate in the chemical reaction, generating water and electrical energy to drive the motor connected to the hydrogen fuel cell 20 and the fan or propeller to provide aircraft thrust.

[0035] Further, the battery circulation unit further comprises a cooling liquid storage tank 23, a cooling liquid pump 24, a cooling liquid filter 25 and a heat exchanger 21, the heat exchanger 21 is used to absorb the waste heat of the hydrogen fuel cell 20 by the cooling liquid, the outlet of the heat exchanger 21 is connected to the first heat exchange side of the third heat exchanger 18, the cooling liquid storage tank 23, the cooling liquid pump 24 and the cooling liquid filter 25 in turn, and is connected back to the inlet of the heat exchanger 21 from the cooling liquid filter 25.

[0036] In the specific embodiment, the heat of the hydrogen fuel cell 20 is taken away by the cooling liquid in the heat exchanger 21, the cooling liquid carrying heat enters the first heat exchange side of the third heat exchanger 18, exchanges heat with the liquid hydrogen in the second heat exchange side of the third heat exchanger 18, and then reenters the heat exchanger 21 after passing through the cooling liquid storage tank 23, the cooling liquid pump 24 and the cooling liquid filter 25 in turn to exchange heat again.

[0037] In one embodiment, the hydrogen fuel engine 11 and the hydrogen fuel cell 20 adopt two different units to provide different hydrogen conditions respectively, so that the system has higher flexibility, reliability and safety, and can also adjust the hydrogen flow according to the flight stage to improve the efficiency of the aircraft.

[0038] Further, the first liquid hydrogen storage tank 1 and the second liquid hydrogen storage tank 13 are respectively provided with a first electric heater 2 and a second electric heater 14.

[0039] In the specific embodiment, the first electric heater 2 and the second electric heater 14 are used to heat the liquid hydrogen, and to dynamically adjust the tank pressure of the first liquid hydrogen storage tank 1 and the second liquid hydrogen storage tank 13, so as to avoid the tank pressure being too low when the liquid hydrogen consumption rate is too high. At the same time, when the ambient heat enters the storage tank and the evaporation rate of the liquid hydrogen is high, the evaporated hydrogen can be discharged to maintain the stable pressure in the storage tank.

[0040] Further, it further comprises a cross-supply hydrogen valve 15, the two ends of the cross-supply hydrogen valve 15 are respectively connected to the group between the first liquid hydrogen storage tank 1 and the first booster pump 4, and the group between the second liquid hydrogen storage tank 13 and the second booster pump 17.

[0041] In the specific embodiment, the cross-supply hydrogen valve 15 is connected to the two liquid hydrogen storage tanks, and the cross-supply hydrogen valve 15 can realize the alternate supply between the first liquid hydrogen storage tank 1 and the second liquid hydrogen storage tank 13, so that the two storage tanks can be used as standby for each other under normal supply conditions, and hydrogen fuel can be provided for the engine circulation unit or the battery circulation unit. When one of the liquid hydrogen storage tanks fails, the cross-supply hydrogen valve 15 can be opened to supply liquid hydrogen from the other liquid hydrogen storage tank, further ensuring safety; or when one side of the engine or battery circulation unit fails, the stop valve or liquid hydrogen supply pipeline of the failed unit can be closed; if the other normally operating unit needs additional hydrogen fuel, the cross-supply hydrogen valve 15 can be opened to supply liquid hydrogen from the liquid hydrogen storage tank of the failed unit to the normally operating unit.

[0042] Further, when the first group of booster pumps 4 includes a plurality of first booster pumps 4, the first liquid hydrogen storage tank 1 is connected to each first booster pump 4 respectively and is connected to the second heat exchange side of the first heat exchanger 5.

[0043] In the specific embodiment, the first booster pump 4 and the second booster pump 17 respectively boost the liquid hydrogen provided by the first liquid hydrogen storage tank 1 and the second liquid hydrogen storage tank 13, so that the liquid hydrogen can be supplied to the hydrogen fuel engine 11. Figure 1 For example, the first group of booster pumps 4 includes two first booster pumps 4, and the two first booster pumps 4 are connected in parallel, which can meet the large flow demand of the hydrogen fuel engine 11.

[0044] Further, the first stop valve 3 and the fourth stop valve 16 are further included, the first stop valve 3 is arranged at the inlet of each first booster pump 4, and the fourth stop valve 16 is arranged at the inlet of the second booster pump 17.

[0045] In the specific embodiment, the first stop valve 3 and the fourth stop valve 16 are respectively used to control the on-off of the first booster pump 4 and the second booster pump 17. When the first stop valve 3 is opened, the liquid hydrogen in the first liquid hydrogen storage tank 1 sequentially passes through, or the liquid hydrogen in the second liquid hydrogen storage tank 13 sequentially passes through the cross-supply hydrogen valve 15, each opened first stop valve 3 and each first booster pump 4, and enters the second heat exchange side of the first heat exchanger 5. When the fourth stop valve 16 is opened, the liquid hydrogen in the second liquid hydrogen storage tank 13 sequentially passes through, or the liquid hydrogen in the first liquid hydrogen storage tank 1 sequentially passes through the cross-supply hydrogen valve 15, the fourth stop valve and the second booster pump 17, and enters the second heat exchange side of the third heat exchanger 18.

[0046] Further, the first flow regulating valve 10 is further included, and the first flow regulating valve 10 is arranged at the inlet of the hydrogen fuel engine 11.

[0047] In the specific embodiment, the first flow regulating valve 10 regulates the flow entering the hydrogen fuel engine 11.

[0048] Further, the second stop valve 7 and the third stop valve 8 are further included, the third stop valve 8 is arranged between the second heat exchange side outlet of the second heat exchanger 6 and the compressor 9, and the third stop valve.

[0049] In the specific embodiment, the second stop valve 7 is used to control the on-off between the second heat exchange side of the second heat exchanger 6 and the hydrogen fuel engine 11, and the third stop valve 8 is used to control the on-off between the second heat exchange side of the second heat exchanger 6 and the compressor 9; when the second stop valve 7 is opened and the third stop valve 8 is closed, the hydrogen gas enters the hydrogen fuel engine 11 after being regulated by the second stop valve 7 and the first flow regulating valve 10; when the third stop valve 8 is opened and the second stop valve 7 is closed, the hydrogen gas enters the hydrogen fuel engine 11 after being regulated by the third stop valve 8 and the compressor 9 and then by the first flow regulating valve 10.

[0050] Further, the second flow regulating valve 19 and the pressure regulating valve 22 are further included, the second flow regulating valve 19 is arranged between the second heat exchange side outlet of the third heat exchanger 18 and the hydrogen fuel cell 20, and the pressure regulating valve 22 is arranged between the first heat exchange side outlet of the third heat exchanger 18 and the cooling liquid storage tank 23.

[0051] In the specific embodiment, the second flow regulating valve 19 is used to regulate the hydrogen gas flow entering the hydrogen fuel cell 20, and the pressure regulating valve 22 is used to regulate the pressure of the cooling liquid, the cooling liquid after being cooled is regulated by the pressure regulating valve 22, and then is sent to the cooling liquid storage tank 23, the cooling liquid pump 24 and the cooling liquid filter 25, and then is sent back to the heat exchanger 21 for further heat exchange.

[0052] Of course, the present application can have other various embodiments, and based on the embodiment, other embodiments obtained by those skilled in the art without any creative labor are within the scope of protection of the present application.

Claims

1. A liquid hydrogen fuel storage and supply system suitable for hybrid hydrogen-powered aircraft, characterized in that: The engine circulation unit includes a first liquid hydrogen storage tank, a first booster pump group, a first heat exchanger, a second heat exchanger, a compressor and a hydrogen fuel engine, wherein: The first boost pump group includes at least one first boost pump; the first heat exchange side of the first heat exchanger and the first heat exchange side of the second heat exchanger are connected to the hydrogen fuel engine and are used to exchange heat with the exhaust gas of the hydrogen fuel engine. The first liquid hydrogen storage tank is connected to the first boost pump group, the second heat exchange side of the first heat exchanger and the second heat exchange side of the second heat exchanger in sequence. One outlet of the second heat exchange side of the second heat exchanger is connected to the compressor and the hydrogen fuel engine in sequence, and the other outlet is directly connected to the hydrogen fuel engine. The liquid hydrogen passes through the second heat exchange side of the first heat exchanger, the second heat exchange side of the second heat exchanger, and the exhaust gas of the first heat exchange side and the first heat exchange side of the second heat exchanger to heat up and gasify, and is compressed by the compressor or directly enters the hydrogen fuel engine.

2. The liquid hydrogen fuel storage and supply system for a hybrid hydrogen-powered aircraft according to claim 1, characterized in that: The device further includes a battery circulation unit, which includes a second liquid hydrogen storage tank, a second boost pump, a third heat exchanger, and a hydrogen fuel cell, wherein: The first heat exchange side of the third heat exchanger is used to exchange heat with the coolant of the hydrogen fuel cell. The second liquid hydrogen storage tank is connected to the second boost pump, the second heat exchange side of the third heat exchanger and the hydrogen fuel cell in sequence. The liquid hydrogen passes through the second heat exchange side of the third heat exchanger and exchanges heat with the coolant on the first heat exchange side of the third heat exchanger to absorb heat, heat up and vaporize, and then enters the hydrogen fuel cell.

3. The liquid hydrogen fuel storage and supply system for a hybrid hydrogen-powered aircraft according to claim 2, characterized in that: The battery circulation unit also includes a coolant storage tank, a coolant pump, a coolant filter and a heat exchanger. The heat exchanger is used to absorb the waste heat of the hydrogen fuel cell through the coolant. The outlet of the heat exchanger is connected to the first heat exchange side of the third heat exchanger, the coolant storage tank, the coolant pump and the coolant filter in sequence, and is connected back to the inlet of the heat exchanger from the coolant filter.

4. The liquid hydrogen fuel storage and supply system for a hybrid hydrogen-powered aircraft according to claim 3, characterized in that: A first electric heater and a second electric heater are respectively provided inside the first liquid hydrogen storage tank and the second liquid hydrogen storage tank.

5. The liquid hydrogen fuel storage and supply system for a hybrid hydrogen-powered aircraft according to claim 4, characterized in that: It also includes a cross-transfer hydrogen supply valve, both ends of which are respectively connected between the first liquid hydrogen storage tank and the first booster pump group and between the second liquid hydrogen storage tank and the second booster pump.

6. The liquid hydrogen fuel storage and supply system for a hybrid hydrogen-powered aircraft according to claim 3, characterized in that: When the first boosting pump group includes a plurality of first boosting pumps, the first liquid hydrogen storage tank is connected to each of the first boosting pumps respectively and connected to the second heat exchange side of the first heat exchanger.

7. The liquid hydrogen fuel storage and supply system for a hybrid hydrogen-powered aircraft according to claim 6, characterized in that: The system further comprises a first stop valve and a fourth stop valve, wherein the first stop valve is arranged on the inlet of each of the first boosting pumps, and the fourth stop valve is arranged on the inlet of the second boosting pump.

8. The liquid hydrogen fuel storage and supply system for a hybrid hydrogen-powered aircraft according to claim 7, characterized in that: It also includes a first flow regulating valve, which is arranged at the inlet of the hydrogen fuel engine.

9. The liquid hydrogen fuel storage and supply system for a hybrid hydrogen-powered aircraft according to claim 8, characterized in that: It also includes a second stop valve and a third stop valve, one end of the second stop valve is connected to the second heat exchange side outlet of the second heat exchanger, and the other end is connected to the inlet of the hydrogen fuel engine, and the third stop valve is arranged between the second heat exchange side outlet of the second heat exchanger and the compressor.

10. The liquid hydrogen fuel storage and supply system for a hybrid hydrogen-powered aircraft according to claim 9, characterized in that: It also includes a second flow regulating valve and a pressure regulating valve. The second flow regulating valve is arranged between the second heat exchange side outlet of the third heat exchanger and the hydrogen fuel cell, and the pressure regulating valve is arranged between the first heat exchange side outlet of the third heat exchanger and the coolant storage tank.

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