Liquid hydrogen fuel storage and supply system suitable for hybrid hydrogen powered aircraft

Abstract

The liquid hydrogen fuel storage and supply system comprises an engine circulation unit, the engine circulation unit comprises a first liquid hydrogen storage tank, a first booster pump set, a first heat exchanger, a second heat exchanger, a compressor and a hydrogen fuel engine, and liquid hydrogen in the first liquid hydrogen storage tank is pressurized through the first booster pump set and then enters the first heat exchanger; waste gas which 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 first heat exchange side of the second heat exchanger exchanges heat, is heated and gasified, and is compressed by a compressor or directly enters a hydrogen fuel engine; different numbers of first booster pumps can be opened according to the actual requirements of the hydrogen fuel engine, hydrogen is pressurized or directly conveyed into the hydrogen fuel engine, hydrogen with different pressures and flows is controlled to be introduced into the hydrogen fuel engine, sufficient combustion of the hydrogen can be guaranteed, and the hydrogen utilization rate is increased.

Description

Technical Field

[0001] The invention relates to the technical field of fuel storage and supply, and in particular to a liquid hydrogen fuel storage and supply system suitable for a hybrid hydrogen-powered aircraft. Background Art

[0002] Hydrogen-powered aircraft have become an important direction for future development. Hydrogen power mainly comes in two forms: hydrogen fuel cells and hydrogen fuel engines. Hydrogen fuel cells only emit water vapor, which is environmentally friendly and efficient, but their energy density is relatively low and their output power is limited. Hydrogen fuel engines have high combustion efficiency and can meet large thrust requirements. Therefore, combining the two can maximize the efficiency of the aircraft at different stages.

[0003] Prior art, such as CN118358761A discloses a main and tail rotor separated full hydrogen hybrid propulsion system suitable for heavy-duty long-range helicopters. It provides a hybrid hydrogen power solution that uses a hydrogen fuel cell to drive the tail propeller alone, thereby reducing the mechanical transmission mechanism, and exchanges heat with the oil for cooling the main propeller motor, tail propeller motor, hydrogen fuel cell, etc. through liquid hydrogen, while achieving the gasification of liquid hydrogen and the cooling of high-temperature equipment. However, the hybrid power system does not take into account the different hydrogen inlet conditions of the hydrogen fuel turboshaft engine and the hydrogen fuel cell. If the different hydrogen inlet conditions in the hydrogen fuel engine and the hydrogen fuel cell are not properly adjusted, part of the hydrogen will not be able to fully burn when it enters the hydrogen fuel engine, thereby reducing the combustion efficiency of the hydrogen, or part of the hydrogen will not be able to react effectively when it enters the hydrogen fuel cell, thereby reducing the efficiency of the hydrogen fuel cell. Summary of the invention

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

[0005] The present invention is achieved through the following technical solutions:

[0006] The present invention proposes a liquid hydrogen fuel storage and supply system suitable for a hybrid hydrogen-powered aircraft, comprising an engine circulation unit, wherein the engine circulation unit

[0007] The invention comprises an engine circulation unit, wherein 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; 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 first heat exchange side of the first heat exchanger, The second heat exchange side of the heat exchanger and the first heat exchange side of the second heat exchanger are heated and gasified, and are compressed by the compressor or directly enter 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 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, wherein the heat exchanger is used to absorb waste heat from the hydrogen fuel cell through coolant, and the outlet of the heat exchanger is sequentially connected to the first heat exchange side of the third heat exchanger, the coolant storage tank, the coolant pump and the coolant filter, and is connected back from the coolant filter to the inlet of the heat exchanger.

[0012] Furthermore, a first electric heater and a second electric heater are respectively disposed 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 between the first liquid hydrogen storage tank and the first boost pump group and between the second liquid hydrogen storage tank and the second boost pump.

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

[0015] Furthermore, it also includes a first stop valve and a fourth stop valve, wherein the first stop valve is arranged on the inlet end of each of the first boosting pumps, and the fourth stop valve is arranged on the inlet end of the second boosting pump.

[0016] Furthermore, it also includes a first flow regulating valve, which is arranged on the inlet of the hydrogen fuel engine.

[0017] Furthermore, 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.

[0018] Furthermore, 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.

[0019] Beneficial effects of the present invention:

[0020] (1) The liquid hydrogen fuel storage and supply system for hybrid hydrogen-powered aircraft proposed in the present invention can open different numbers of first boosting pumps according to the actual needs of the hydrogen fuel engine and subsequently select to boost the hydrogen or directly transport it to the hydrogen fuel engine, thereby controlling the introduction of hydrogen with different pressures and flow rates into the hydrogen fuel engine, thereby ensuring the full combustion of the hydrogen and improving the utilization rate of the hydrogen.

[0021] (2) The cross-transfer hydrogen supply valve of the liquid hydrogen fuel storage and supply system suitable for hybrid hydrogen-powered aircraft proposed in the present invention connects the first liquid hydrogen storage tank and the second liquid hydrogen storage tank, and can realize alternating transmission between the first liquid hydrogen storage tank and the second liquid hydrogen storage tank, so that the two tanks can serve as backup for each other under normal supply conditions to provide hydrogen fuel for the engine circulation unit or the battery circulation unit. When one of the liquid hydrogen storage tanks fails, the cross-transfer hydrogen supply valve can be opened to allow the other liquid hydrogen storage tank to provide liquid hydrogen, further ensuring safety; or when the engine or battery circulation unit on one side fails, the shut-off valve or liquid hydrogen delivery pipeline of the failed unit can be closed. If the other normally working unit needs additional hydrogen fuel, the cross-transfer hydrogen supply valve can be opened to allow the liquid hydrogen in the liquid hydrogen storage tank of the failed unit to be delivered to the normally working unit.

[0022] (3) The liquid hydrogen fuel storage and supply system for hybrid hydrogen-powered aircraft proposed in the present invention uses two different units for the hydrogen fuel cell and the hydrogen fuel engine to provide different hydrogen conditions respectively, thereby making the system more flexible, reliable and safer, and being able to adjust the hydrogen flow rate according to the flight phase to improve the energy efficiency of the aircraft.

[0023] (4) The present invention proposes heat exchange between the coolant and liquid hydrogen in the hydrogen fuel cell, thereby achieving the purpose of coolant heat dissipation and liquid hydrogen gasification, reducing the necessary equipment and its weight, and having a significant impact on increasing the mass hydrogen storage ratio of the liquid hydrogen fuel storage and supply system. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a structural diagram of a liquid hydrogen fuel storage and supply system applicable to a hybrid hydrogen-powered aircraft of the present invention;

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

[0026] The implementation mode, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0027] In order to more clearly and completely illustrate the technical solution of the present invention, the present invention is further described below in conjunction with the accompanying drawings.

[0028] Please refer to Figure 1 The present invention proposes a liquid hydrogen fuel storage and supply system suitable for a hybrid hydrogen-powered aircraft, comprising an engine circulation unit, the engine circulation unit comprising 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 boost pump group 4 includes at least one first boost 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 are used to exchange heat with the exhaust gas of the hydrogen fuel engine 11; the first liquid hydrogen storage tank 1 is connected to the first boost pump group 4, the second heat exchange side 6 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 passes through the second heat exchange side of the first heat exchanger 5, the second heat exchange side of the second heat exchanger 6, and the first heat exchange side of the first heat exchanger 5, the first heat exchange side of the second heat exchanger 6. The exhaust gas is heated and gasified, and is compressed by the compressor 9 or directly enters the hydrogen fuel engine 11.

[0030] In a specific embodiment, the first heat exchanger 5 and the second heat exchanger 6 are heat exchangers located at the tail of the engine in high temperature areas 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 to the first heat exchanger 5 and the second heat exchanger 6. Liquid hydrogen is extracted from the first liquid hydrogen storage tank 1 and is pressurized by the first boost pump 4 group to overcome the pressure drop of the liquid hydrogen along the transportation pipeline.

[0031] Since the hydrogen inlet temperature of the hydrogen fuel engine 11 is relatively high, the liquid hydrogen is first preheated through the second heat exchange side of the first heat exchanger 5 to start gasification, and the hydrogen fuel engine 11 is cooled down during gasification; then, the hydrogen fuel is further heated in the second heat exchange side of the second heat exchanger 6 to completely gasify it, and the temperature is finely controlled in the second heat exchanger 6 to ensure that the hydrogen 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 relatively large, the first booster pump 4 group opens multiple first booster pumps 4, and the hydrogen is pressurized again by the compressor 9 after heat exchange through the first heat exchanger 5 and the second heat exchanger 6 and enters the hydrogen fuel engine 11; when the flow demand of the hydrogen fuel engine 11 is relatively small, the first booster pump 4 group opens one first booster pump 4, and the hydrogen directly enters the hydrogen fuel engine 11 after heat exchange through the first heat exchanger 5 and the second heat exchanger 6. The hydrogen enters the hydrogen fuel engine 11 and burns, and the high-temperature and high-pressure combustion gas generated expands in the turbine to generate mechanical energy, thereby driving the fan or propeller to provide aircraft thrust. Supplying hydrogen in two ways can ensure that the hydrogen is fully burned in the combustion chamber of the hydrogen fuel engine 11 and mixed with air, thereby increasing the gas density and promoting combustion efficiency. The present invention can select hydrogen with different pressures and flow rates according to the actual needs of the hydrogen fuel engine 11 to ensure the full combustion of the hydrogen and improve the utilization rate of the hydrogen.

[0032] Furthermore, it also includes a battery circulation unit, which includes a second liquid hydrogen storage tank 13, a second boost 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 to exchange heat with the coolant of the hydrogen fuel cell 20. The second liquid hydrogen storage tank 13 is connected to the second boost pump 17, the second heat exchange side of the third heat exchanger 18 and the hydrogen fuel cell 20 in sequence. The liquid hydrogen passes through the second heat exchange side of the third heat exchanger 18 and the coolant on the first heat exchange side of the third heat exchanger 18 to absorb heat, heat up and vaporize, and then enters the hydrogen fuel cell 20.

[0034] In a specific embodiment, the second boost pump 17 is used to overcome the pressure drop along the pipeline transportation process. After the liquid hydrogen in the second liquid hydrogen storage tank 13 is pressurized by the second boost pump 17, it is heated and gasified into hydrogen on 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, generate water and electricity, and drive the electric motor connected to the hydrogen fuel cell 20 and the fan or propeller to provide aircraft thrust.

[0035] Furthermore, the battery circulation unit also includes a coolant storage tank 23, a coolant pump 24, a coolant filter 25 and a heat exchanger 21. The heat exchanger 21 is used to absorb waste heat from the hydrogen fuel cell 20 through the coolant. The outlet of the heat exchanger 21 is connected to the first heat exchange side of the third heat exchanger 18, the coolant storage tank 23, the coolant pump 24 and the coolant filter 25 in sequence, and is connected back from the coolant filter 25 to the inlet of the heat exchanger 21.

[0036] In a specific embodiment, the heat of the hydrogen fuel cell 20 is taken away by the coolant in the heat exchanger 21, and the coolant carrying the heat enters the first heat exchange side of the third heat exchanger 18, and exchanges heat with the liquid hydrogen in the second heat exchange side of the third heat exchanger 18. After the temperature of the coolant is reduced, it passes through the coolant storage tank 23, the coolant pump 24 and the coolant filter 25 in sequence and then returns to the heat exchanger 21 for heat exchange again.

[0037] In one embodiment, the hydrogen fuel engine 11 and the hydrogen fuel cell 20 use 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 phase to improve the energy efficiency of the aircraft.

[0038] Furthermore, a first electric heater 2 and a second electric heater 14 are respectively disposed inside the first liquid hydrogen storage tank 1 and the second liquid hydrogen storage tank 13 .

[0039] In a specific embodiment, the first electric heater 2 and the second electric heater 14 are used to heat the liquid hydrogen and dynamically adjust the tank pressure of the first liquid hydrogen storage tank 1 and the second liquid hydrogen storage tank 13 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 tank and the liquid hydrogen evaporation rate is high, the evaporated hydrogen can be discharged to maintain the pressure in the tank stable.

[0040] Furthermore, it also includes a cross-transfer hydrogen supply valve 15, and both ends of the cross-transfer hydrogen supply valve 15 are respectively connected to between the first liquid hydrogen storage tank 1 and the first boosting pump 4 group and between the second liquid hydrogen storage tank 13 and the second boosting pump 17.

[0041] In a specific embodiment, the cross-transmission hydrogen supply valve 15 connects the two liquid hydrogen storage tanks to achieve alternating transmission between the first liquid hydrogen storage tank 1 and the second liquid hydrogen storage tank 13, so that the two tanks can serve as backup for each other under normal supply conditions to provide hydrogen fuel for the engine circulation unit or the battery circulation unit. When one of the liquid hydrogen storage tanks fails, the cross-transmission hydrogen supply valve 15 can be opened to allow the other liquid hydrogen storage tank to provide liquid hydrogen to further ensure safety; or when the engine or battery circulation unit on one side fails, the shut-off valve or liquid hydrogen delivery pipeline of the failed unit can be closed; if another normal working unit needs additional hydrogen fuel, the cross-transmission hydrogen supply valve 15 can be opened to allow the liquid hydrogen in the liquid hydrogen storage tank of the failed unit to be delivered to the normal working unit.

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

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

[0044] Furthermore, it also includes a first stop valve 3 and a fourth stop valve 16 , wherein the first stop valve 3 is arranged on the inlet of each of the first boosting pumps 4 , and the fourth stop valve 16 is arranged on the inlet of the second boosting pump 17 .

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

[0046] Furthermore, it also includes a first flow regulating valve 10 , which is arranged on the inlet of the hydrogen fuel engine 11 .

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

[0048] Furthermore, it also includes a second stop valve 7 and a third stop valve 8. The third stop valve 8 is arranged between the second heat exchange side outlet of the second heat exchanger 6 and the compressor 9.

[0049] In a 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 enters the hydrogen fuel engine 11 after the flow is adjusted 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 enters the hydrogen fuel engine 11 after the flow is adjusted by the third stop valve 8 and the compressor 9.

[0050] Furthermore, it also includes a second flow regulating valve 19 and a pressure regulating valve 22. 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 coolant storage tank 23.

[0051] In a specific embodiment, the second flow regulating valve 19 is used to regulate the flow of hydrogen entering the hydrogen fuel cell 20, and the pressure regulating valve 22 is used to regulate the pressure of the coolant. After the coolant temperature is reduced, the pressure is adjusted by the pressure regulating valve 22, and after passing through the subsequent coolant storage tank 23, coolant pump 24 and coolant filter 25, it returns to the heat exchanger 21 for heat exchange again.

[0052] Of course, the present invention may have many other implementations. Based on this implementation, other implementations obtained by ordinary technicians in this field without any creative work are all within the scope of protection of the present invention.

Claims

1. A liquid hydrogen fuel storage and supply system suitable for a hybrid hydrogen-powered aircraft, characterized in that: The invention comprises an engine circulation unit, wherein 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: 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; 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 first heat exchange side of the first heat exchanger, The second heat exchange side of the heat exchanger and the first heat exchange side of the second heat exchanger are heated and gasified, and are compressed by the compressor or directly enter the hydrogen fuel engine.

2. The liquid hydrogen fuel storage and supply system suitable for a hybrid hydrogen-powered aircraft according to claim 1, characterized in that: 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: 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 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 suitable 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 from the coolant filter to the inlet of the heat exchanger.

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

5. The liquid hydrogen fuel storage and supply system suitable 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 to between the first liquid hydrogen storage tank and the first boost pump group and between the second liquid hydrogen storage tank and the second boost pump.

6. The liquid hydrogen fuel storage and supply system suitable 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 respectively connected to each of the first boosting pumps 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: It also includes 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 suitable 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 suitable 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, wherein 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 suitable 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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