Energy transmission and supply system and control method for a hydrogen-powered aircraft

Abstract

The present application belongs to the field of aircraft power technology, and relates to an energy transfer and supply system and a control method for a hydrogen-powered aircraft. Part of the liquid hydrogen in a liquid hydrogen storage tank is vaporized after absorbing waste heat from electronic equipment, hydraulic oil and lubricating oil heat exchangers, and is sent to fuel cell thermal management through a hydrogen circulation pump for pressure boosting, and is further sent to a fuel cell for power generation after being heated and warmed. Another part is sent to a hydrogen fuel engine, and is combusted in an engine combustion chamber after absorbing heat from engine turbine blades. The system can fully utilize the heat sink of liquid hydrogen while efficiently transferring and supplying liquid hydrogen from a low-temperature storage tank to a hydrogen fuel cell / hydrogen fuel engine, and has the advantages of high flexibility and strong regulation capacity.

Description

Technical Field

[0001] This invention belongs to the field of aircraft propulsion technology, and relates to an energy transmission and supply system and control method for a hydrogen-powered aircraft. Background Technology

[0002] New energy aviation is a crucial support for achieving my country's "dual carbon" goals and energy transition strategy. However, based on advancements in existing traditional aviation technologies, the goal of sustainable development in the aviation industry and reducing carbon emissions to 50% of 2005 levels by 2050 will not be achievable. Therefore, developing sustainable aviation technologies, including replacing traditional aviation kerosene with green energy sources such as hydrogen fuel, biofuels, and solar energy, and adopting advanced technologies such as electric aircraft and blended wing-body designs, will become important tasks for the aviation industry to achieve its carbon reduction targets.

[0003] Hydrogen fuel has advantages such as wide availability, high energy efficiency, and no pollution byproducts, making it a major alternative energy source for future new energy. The application of hydrogen fuel in aircraft mainly takes two forms: hydrogen fuel cells and hydrogen fuel engines. A hydrogen fuel cell is an energy conversion device that directly converts the chemical energy of hydrogen fuel into electrical and thermal energy, while a hydrogen fuel engine directly uses the internal energy released by burning hydrogen fuel to convert it into propulsion work or electrical energy.

[0004] Because cryogenic liquid hydrogen has a mass storage density 14 times that of high-pressure gaseous hydrogen, it is the preferred hydrogen storage solution for future long-range aircraft. Simultaneously, liquid hydrogen will serve as an effective heat sink for the entire aircraft's thermal management. With recent technological breakthroughs in liquid hydrogen storage and hydrogen fuel cell engines, the successful development of hydrogen-powered aircraft is expected within the next five to ten years. To achieve the efficient utilization of liquid hydrogen from cryogenic storage systems to hydrogen fuel cells / engines, this invention provides an energy transfer and supply system and control method for hydrogen-powered aircraft. Summary of the Invention

[0005] The purpose of this invention is to achieve efficient utilization of liquid hydrogen from cryogenic storage systems to hydrogen fuel cells / hydrogen fuel engines. This invention provides an energy transfer and supply system and control method for hydrogen-powered aircraft. Part of the liquid hydrogen in the liquid hydrogen storage tank enters the electronic equipment, hydraulic oil, and lubricating oil heat exchanger to absorb waste heat from the equipment and then vaporizes. After being pressurized by a hydrogen circulation pump, it is sent to the fuel cell thermal management system, where it absorbs heat and is then sent to the fuel cell to generate electricity. The other part is sent to the hydrogen fuel engine, where it absorbs heat from the engine turbine blades and then enters the engine combustion chamber for combustion.

[0006] The technical solution of the present invention: In order to achieve the above-mentioned objective, according to the first aspect of the present invention, an energy transfer and supply system for a hydrogen-powered aircraft is provided, including a liquid hydrogen storage tank 1, a shut-off valve 2, a first flow regulating valve 3, a hydrogen circulation pump 7, a pressure sensor 8, a fuel cell thermal management device 9, a fuel cell 10, an air compressor 11, a back pressure valve 12, a second flow regulating valve 14, a first check valve 15, a third flow regulating valve 16, a hydrogen engine heat exchange device 17, a bypass flow regulating valve 18, a second check valve 19, a hydrogen engine combustion chamber 20, and a controller 21;

[0007] Among them, the fuel cell thermal management device 9 is equipped with a hydrogen inlet, a hydrogen outlet, a heat exchange channel inlet, and a heat exchange channel outlet, while the fuel cell 10 is equipped with a hydrogen inlet, a compressed air inlet, a cooling channel inlet, a cooling channel outlet, a reaction gas outlet, and an electrical load output.

[0008] The outlet of the liquid hydrogen storage tank 1 is connected to the inlet of the shut-off valve 2 via a pipeline. The outlet of the shut-off valve 2 is divided into three paths via a four-way pipe. One path is connected to the inlet of the first flow regulating valve 3, the second path is connected to the inlet of the second flow regulating valve 14, and the third path is connected to the inlet of the third flow regulating valve 16. The outlet of the first flow regulating valve 3 is divided into two paths. One path is connected to the inlet of the hydrogen circulation pump 7 via a pipeline, and the other path is connected to the inlet of the bypass flow regulating valve 18 via a pipeline.

[0009] The outlet of the second flow regulating valve 14 is connected to the inlet of the first check valve 15 via a pipeline. The outlet of the first check valve 15 and the outlet of the hydrogen circulation pump 7 are connected to the hydrogen inlet of the fuel cell thermal management device 9 via a three-way pipe. The hydrogen outlet of the fuel cell thermal management device 9 is connected to the hydrogen inlet of the fuel cell 10 via a pipeline. The inlet of the heat exchange channel of the fuel cell thermal management device 9 is connected to the outlet of the cooling channel of the fuel cell 10 via a pipeline. The outlet of the heat exchange channel of the fuel cell thermal management device 9 is connected to the inlet of the cooling channel of the fuel cell 10 via a pipeline.

[0010] The outlet of the air compressor 11 is connected to the compressed air inlet of the fuel cell 10 via a pipe, and the reactant gas outlet of the fuel cell 10 is connected to the back pressure valve 12 via a pipe.

[0011] The outlet of the third flow regulating valve 16 is connected to the inlet of the hydrogen engine heat exchanger 17 via a pipeline. The outlet of the bypass flow regulating valve 18 is connected to the inlet of the second check valve 19 via a pipeline. The outlet of the second check valve 19 and the outlet of the hydrogen engine heat exchanger 17 are connected to the inlet of the hydrogen engine combustion chamber 20 via a three-way pipe.

[0012] The pressure sensor 8 is connected to the sampling port on the pipeline between the hydrogen circulation pump 7 and the fuel cell thermal management device 9;

[0013] The controller 21 includes a signal input terminal and a signal output terminal. The shut-off valve 2, the first flow regulating valve 3, the hydrogen circulation pump 7, the air compressor 11, the second flow regulating valve 14, the third flow regulating valve 16, and the bypass flow regulating valve 18 are connected to the signal input terminal of the controller 21 via cables; the pressure sensor 8 is connected to the signal output terminal of the controller 21 via a cable.

[0014] In one possible embodiment, it also includes an electronic device heat exchanger 4, a hydraulic oil heat exchanger 5, and a lubricating oil heat exchanger 6. The outlet of the first flow regulating valve 3 is connected in sequence to the inlets of the electronic device heat exchanger 4, the hydraulic oil heat exchanger 5, and the lubricating oil heat exchanger 6 via pipelines.

[0015] In one possible embodiment, a liquid water collector 13 is also included, which is connected to the outlet of the back pressure valve 12 via a pipe.

[0016] According to a second aspect of the present invention, a control method for an energy transmission and supply system of a hydrogen-powered aircraft is provided, which employs the aforementioned energy transmission and supply system for a hydrogen-powered aircraft and specifically includes the following steps:

[0017] (1) The controller 21 receives real-time status information of various equipment on the aircraft, the liquid hydrogen flow rate required for real-time heat dissipation of electronic equipment, hydraulic oil and lubricating oil on the computer, and the hydrogen supply flow rate required for the fuel cell 10 to generate electricity for the onboard electrical equipment.

[0018] (2) When the system is initially started, the signal output terminal of controller 21 sends an opening command to the shut-off valve 2, the first flow regulating valve 3, and the third flow regulating valve 16, and sends a closing command to the second flow regulating valve 14 and the bypass flow regulating valve 18; the signal output terminal of controller 21 sends a start signal to start the hydrogen circulation pump 7 and the air compressor 11.

[0019] (3) Determine the relationship between the liquid hydrogen flow rate required for cooling the electronic equipment, hydraulic oil, and lubricating oil and the hydrogen supply flow rate required for the fuel cell 10: When the liquid hydrogen flow rate required for cooling the electronic equipment, hydraulic oil, and lubricating oil is less than the hydrogen supply flow rate required for the fuel cell 10, close the bypass flow regulating valve 18, open and adjust the second flow regulating valve 14 to the valve opening degree corresponding to the difference in the required flow rates; when the liquid hydrogen flow rate required for cooling the electronic equipment, hydraulic oil, and lubricating oil is greater than the hydrogen supply flow rate required for the fuel cell 10, close the second flow regulating valve 14, open and adjust the bypass flow regulating valve 18 to the valve opening degree corresponding to the difference in the required flow rates; when the liquid hydrogen flow rate required for cooling the electronic equipment, hydraulic oil, and lubricating oil is equal to the hydrogen supply flow rate required for the fuel cell 10, close the second flow regulating valve 14 and the bypass flow regulating valve 18.

[0020] (4) The signal input terminal of the controller 21 receives the pressure information from the pressure sensor 8. When the hydrogen pressure monitored by the pressure sensor 8 is lower than the lower limit of the set value, the signal output terminal of the controller 21 sends an adjustment signal to the hydrogen circulation pump 7 to increase the speed of the hydrogen circulation pump 7. When the hydrogen pressure monitored by the pressure sensor 8 is higher than the upper limit of the set value, the signal output terminal of the controller 21 sends an adjustment signal to the hydrogen circulation pump 7 to decrease the speed of the hydrogen circulation pump 7. When the hydrogen pressure monitored by the pressure sensor 8 is within the upper and lower limits of the set value, the controller 21 does not need to send an adjustment signal, and the speed of the hydrogen circulation pump 7 remains unchanged.

[0021] According to a third aspect of the present invention, a hydrogen-powered aircraft is provided, characterized in that it includes an energy transmission and supply system for the hydrogen-powered aircraft.

[0022] Compared with the prior art, the present invention has the following technical features:

[0023] 1. In view of the different application requirements of hydrogen fuel cells and hydrogen fuel engines on aircraft, this invention provides an energy transfer and supply system for liquid hydrogen storage, which can realize the efficient utilization of liquid hydrogen from cryogenic storage system to hydrogen fuel cell / hydrogen fuel engine.

[0024] 2. After being discharged from the liquid hydrogen storage tank, part of the liquid hydrogen enters the electronic equipment, hydraulic oil and lubricating oil heat exchanger in sequence to absorb the waste heat of the electronic equipment, hydraulic oil and lubricating oil on the machine, and then enters the fuel cell to participate in the thermal management of the fuel cell; another part of the liquid hydrogen enters the hydrogen fuel engine, and after cooling the engine turbine blades, it enters the combustion chamber. This hydrogen energy transfer and supply system makes full use of the heat sink of liquid hydrogen.

[0025] 3. The liquid hydrogen delivery system of this system is divided into three routes. When the waste heat of the on-board heat exchange equipment is large and a large amount of liquid hydrogen heat sink is required, some of the vaporized hydrogen can be sent to the hydrogen fuel engine. When the liquid hydrogen heat sink required by the on-board heat exchange equipment is small, some of the liquid hydrogen can be directly sent to the fuel cell to participate in the fuel cell thermal management. It has the advantages of high flexibility and strong adjustment capability. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of an energy transfer and supply system and control method for a hydrogen-powered aircraft according to the present invention.

[0027] Among them, 1-liquid hydrogen storage tank, 2-stop valve, 3-first flow regulating valve, 4-electronic equipment heat exchanger, 5-hydraulic oil heat exchanger, 6-lubricating oil heat exchanger, 7-hydrogen circulation pump, 8-pressure sensor, 9-fuel cell thermal management equipment, 10-fuel cell, 11-air compressor, 12-back pressure valve, 13-liquid water collector, 14-second flow regulating valve, 15-first check valve, 16-third flow regulating valve, 17-hydrogen engine heat exchange equipment, 18-bypass flow regulating valve, 19-second check valve, 20-hydrogen engine combustion chamber, 21-controller. Detailed Implementation

[0028] The present invention will be further described below with reference to embodiments. These descriptions are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0029] The following is an embodiment of the present invention:

[0030] like Figure 1 As shown, an energy transfer and supply system for a hydrogen-powered aircraft according to the present invention includes a liquid hydrogen storage tank 1, a shut-off valve 2, a first flow regulating valve 3, an electronic device heat exchanger 4, a hydraulic oil heat exchanger 5, a lubricating oil heat exchanger 6, a hydrogen circulation pump 7, a pressure sensor 8, a fuel cell thermal management device 9, a fuel cell 10, an air compressor 11, a back pressure valve 12, a liquid water collector 13, a second flow regulating valve 14, a first check valve 15, a third flow regulating valve 16, a hydrogen engine heat exchange device 17, a bypass flow regulating valve 18, a second check valve 19, a hydrogen engine combustion chamber 20, and a controller 21.

[0031] Among them, the fuel cell thermal management device 9 is equipped with a hydrogen inlet, a hydrogen outlet, a heat exchange channel inlet, and a heat exchange channel outlet, while the fuel cell 10 is equipped with a hydrogen inlet, a compressed air inlet, a cooling channel inlet, a cooling channel outlet, a reaction gas outlet, and an electrical load output.

[0032] The outlet of the liquid hydrogen storage tank 1 is connected to the inlet of the shut-off valve 2 via a pipeline. The outlet of the shut-off valve 2 is divided into three paths via a four-way pipe. One path is connected to the inlet of the first flow regulating valve 3, the second path is connected to the inlet of the second flow regulating valve 14, and the third path is connected to the inlet of the third flow regulating valve 16. The outlet of the first flow regulating valve 3 is connected to the inlets of the electronic equipment heat exchanger 4, the hydraulic oil heat exchanger 5, and the lubricating oil heat exchanger 6 in sequence via pipelines. The outlet of the lubricating oil heat exchanger 6 is divided into two paths via a three-way pipe. One path is connected to the inlet of the hydrogen circulation pump 7 via a pipeline, and the other path is connected to the inlet of the bypass flow regulating valve 18 via a pipeline.

[0033] Among them, the first flow regulating valve 3, the second flow regulating valve 14, the third flow regulating valve 16, and the bypass flow regulating valve 18 are all electrically operated regulating valves; the electronic equipment heat exchanger 4, the hydraulic oil heat exchanger 5, and the lubricating oil heat exchanger 6 are used to absorb the waste heat of the refrigerant, hydraulic oil, and lubricating oil of the high-temperature electronic equipment on the aircraft; when the liquid hydrogen flow rate required for cooling of the electronic equipment, hydraulic oil, and lubricating oil on the aircraft is less than the hydrogen supply flow rate required by the fuel cell 10, the bypass flow regulating valve 18 is closed, and the second flow regulating valve 14 is opened and adjusted to the valve opening degree corresponding to the difference between the two required flow rates; when the liquid hydrogen flow rate required for cooling of the electronic equipment, hydraulic oil, and lubricating oil on the aircraft is greater than the hydrogen supply flow rate required by the fuel cell 10, the second flow regulating valve 14 is closed, and the bypass flow regulating valve 18 is opened and adjusted to the valve opening degree corresponding to the difference between the two required flow rates; when the liquid hydrogen flow rate required for cooling of the electronic equipment, hydraulic oil, and lubricating oil on the aircraft is equal to the hydrogen supply flow rate required by the fuel cell 10, the second flow regulating valve 14 and the bypass flow regulating valve 18 are closed.

[0034] The outlet of the second flow regulating valve 14 is connected to the inlet of the first check valve 15 via a pipeline. The outlet of the first check valve 15 and the outlet of the hydrogen circulation pump 7 are connected to the hydrogen inlet of the fuel cell thermal management device 9 via a three-way pipe. The hydrogen outlet of the fuel cell thermal management device 9 is connected to the hydrogen inlet of the fuel cell 10 via a pipeline. The inlet of the heat exchange channel of the fuel cell thermal management device 9 is connected to the outlet of the cooling channel of the fuel cell 10 via a pipeline. The outlet of the heat exchange channel of the fuel cell thermal management device 9 is connected to the inlet of the cooling channel of the fuel cell 10 via a pipeline.

[0035] Among them, the hydrogen circulation pump 7 is a variable frequency pump with adjustable speed, used to pressurize and deliver the hydrogen from the outlet of the lubricating oil heat exchanger 6 to the hydrogen inlet of the fuel cell 10; the fuel cell 10 refers to a proton exchange membrane type low-temperature fuel cell or a solid oxide type high-temperature fuel cell, which can directly convert the chemical energy of hydrogen fuel into electrical energy and heat energy, and has the advantage of high energy conversion rate.

[0036] The outlet of the air compressor 11 is connected to the compressed air inlet of the fuel cell 10 via a pipe, and the reaction gas outlet of the fuel cell 10 is connected to the back pressure valve 12 via a pipe; (wherein, the back pressure valve 12 is used to maintain the pressure environment inside the fuel cell 10).

[0037] The outlet of the third flow regulating valve 16 is connected to the inlet of the hydrogen engine heat exchanger 17 via a pipeline. The outlet of the bypass flow regulating valve 18 is connected to the inlet of the second check valve 19 via a pipeline. The outlet of the second check valve 19 and the outlet of the hydrogen engine heat exchanger 17 are connected to the inlet of the hydrogen engine combustion chamber 20 via a three-way pipe.

[0038] Among them, the hydrogen engine heat exchange equipment 17 refers to the hydrogen engine turbine blades. Liquid hydrogen is used to cool the hydrogen engine turbine blades to increase the turbine inlet gas temperature, which can effectively improve engine performance, such as increasing engine thrust, improving engine efficiency and power-to-weight ratio.

[0039] An energy transfer and supply system for a hydrogen-powered aircraft also includes a pressure sensor 8, which is connected to a sampling port on a pipeline between the hydrogen circulation pump 7 and the fuel cell thermal management device 9; wherein, the pressure sensor 8 is used to monitor the hydrogen pressure entering the hydrogen inlet of the fuel cell 10.

[0040] An energy transfer and supply system for a hydrogen-powered aircraft also includes a liquid water collector 13, which is connected to the outlet of a back pressure valve 12 via a pipeline. The liquid water collector 13 is used to collect water vapor generated by the reaction and liquefy it into water for recycling, thereby reducing the weight compensation loss caused by the aircraft carrying extra water.

[0041] An energy transmission and supply system for a hydrogen-powered aircraft also includes a controller 21, which includes a signal input terminal and a signal output terminal. The shut-off valve 2, the first flow regulating valve 3, the hydrogen circulation pump 7, the air compressor 11, the second flow regulating valve 14, the third flow regulating valve 16, and the bypass flow regulating valve 18 are connected to the signal input terminal of the controller 21 via cables; the pressure sensor 8 is connected to the signal output terminal of the controller 21 via a cable.

[0042] Specifically, a control method for the energy transmission and supply system of a hydrogen-powered aircraft is as follows:

[0043] (1) The controller 21 receives real-time status information of various equipment on the aircraft, the liquid hydrogen flow rate required for real-time heat dissipation of electronic equipment, hydraulic oil and lubricating oil on the computer, and the hydrogen supply flow rate required for the fuel cell 10 to generate electricity for the onboard electrical equipment.

[0044] (2) When the system is initially started, the signal output terminal of controller 21 sends an opening command to the shut-off valve 2, the first flow regulating valve 3, and the third flow regulating valve 16, and sends a closing command to the second flow regulating valve 14 and the bypass flow regulating valve 18; the signal output terminal of controller 21 sends a start signal to start the hydrogen circulation pump 7 and the air compressor 11.

[0045] (3) Determine the relationship between the liquid hydrogen flow rate required for cooling the electronic equipment, hydraulic oil, and lubricating oil and the hydrogen supply flow rate required for the fuel cell 10: When the liquid hydrogen flow rate required for cooling the electronic equipment, hydraulic oil, and lubricating oil is less than the hydrogen supply flow rate required for the fuel cell 10, close the bypass flow regulating valve 18, open and adjust the second flow regulating valve 14 to the valve opening degree corresponding to the difference in the required flow rates; when the liquid hydrogen flow rate required for cooling the electronic equipment, hydraulic oil, and lubricating oil is greater than the hydrogen supply flow rate required for the fuel cell 10, close the second flow regulating valve 14, open and adjust the bypass flow regulating valve 18 to the valve opening degree corresponding to the difference in the required flow rates; when the liquid hydrogen flow rate required for cooling the electronic equipment, hydraulic oil, and lubricating oil is equal to the hydrogen supply flow rate required for the fuel cell 10, close the second flow regulating valve 14 and the bypass flow regulating valve 18.

[0046] (4) The signal input terminal of the controller 21 receives the pressure information from the pressure sensor 8. When the hydrogen pressure monitored by the pressure sensor 8 is lower than the lower limit of the set value, the signal output terminal of the controller 21 sends an adjustment signal to the hydrogen circulation pump 7 to increase the speed of the hydrogen circulation pump 7. When the hydrogen pressure monitored by the pressure sensor 8 is higher than the upper limit of the set value, the signal output terminal of the controller 21 sends an adjustment signal to the hydrogen circulation pump 7 to decrease the speed of the hydrogen circulation pump 7. When the hydrogen pressure monitored by the pressure sensor 8 is within the upper and lower limits of the set value, the controller 21 does not need to send an adjustment signal, and the speed of the hydrogen circulation pump 7 remains unchanged.

Claims

1. An energy transmission and supply system for a hydrogen-powered aircraft, characterized in that, Includes a liquid hydrogen storage tank (1), a shut-off valve (2), a first flow regulating valve (3), a hydrogen circulation pump (7), a pressure sensor (8), a fuel cell thermal management device (9), a fuel cell (10), an air compressor (11), a back pressure valve (12), a second flow regulating valve (14), a first check valve (15), a third flow regulating valve (16), a hydrogen engine heat exchange device (17), a bypass flow regulating valve (18), a second check valve (19), a hydrogen engine combustion chamber (20), and a controller (21); Among them, the fuel cell thermal management device (9) is provided with a hydrogen inlet, a hydrogen outlet, a heat exchange channel inlet, and a heat exchange channel outlet, and the fuel cell (10) is provided with a hydrogen inlet, a compressed air inlet, a cooling channel inlet, a cooling channel outlet, a reaction gas outlet, and an electrical load output. The outlet of the liquid hydrogen storage tank (1) is connected to the inlet of the shut-off valve (2) through a pipeline. The outlet of the shut-off valve (2) is divided into three paths through a four-way pipe. One path is connected to the inlet of the first flow regulating valve (3), the second path is connected to the inlet of the second flow regulating valve (14), and the third path is connected to the inlet of the third flow regulating valve (16). The outlet of the first flow regulating valve (3) is divided into two paths. One path is connected to the inlet of the hydrogen circulation pump (7) through a pipeline, and the other path is connected to the inlet of the bypass flow regulating valve (18) through a pipeline. The outlet of the second flow regulating valve (14) is connected to the inlet of the first check valve (15) through a pipe. The outlet of the first check valve (15) and the outlet of the hydrogen circulation pump (7) are connected through a three-way pipe and then connected to the hydrogen inlet of the fuel cell thermal management device (9). The hydrogen outlet of the fuel cell thermal management device (9) is connected to the hydrogen inlet of the fuel cell (10) through a pipe. The inlet of the heat exchange channel of the fuel cell thermal management device (9) is connected to the outlet of the cooling channel of the fuel cell (10) through a pipe. The outlet of the heat exchange channel of the fuel cell thermal management device (9) is connected to the inlet of the cooling channel of the fuel cell (10) through a pipe. The outlet of the air compressor (11) is connected to the compressed air inlet of the fuel cell (10) via a pipe, and the outlet of the fuel cell (10) reactant gas is connected to the back pressure valve (12) via a pipe. The outlet of the third flow regulating valve (16) is connected to the inlet of the hydrogen engine heat exchanger (17) through a pipe. The outlet of the bypass flow regulating valve (18) is connected to the inlet of the second check valve (19) through a pipe. The outlet of the second check valve (19) and the outlet of the hydrogen engine heat exchanger (17) are connected to the inlet of the hydrogen engine combustion chamber (20) through a three-way pipe. The pressure sensor (8) is connected to the sampling port on the pipeline between the hydrogen circulation pump (7) and the fuel cell thermal management device (9); The controller (21) is connected in communication with the shut-off valve (2), the first flow regulating valve (3), the hydrogen circulation pump (7), the air compressor (11), the second flow regulating valve (14), the third flow regulating valve (16), the bypass flow regulating valve (18), and the pressure sensor (8). It also includes an electronic device heat exchanger (4), a hydraulic oil heat exchanger (5), a lubricating oil heat exchanger (6), and the outlet of the first flow regulating valve (3) is connected to the inlet of the electronic device heat exchanger (4), the hydraulic oil heat exchanger (5), and the lubricating oil heat exchanger (6) in sequence through a pipeline.

2. The energy transmission and supply system for a hydrogen-powered aircraft according to claim 1, characterized in that, It also includes a liquid water collector (13), which is connected to the outlet of the back pressure valve (12) via a pipe.

3. The energy transmission and supply system for a hydrogen-powered aircraft according to claim 1, characterized in that, The controller (21) includes a signal input terminal and a signal output terminal. The shut-off valve (2), the first flow regulating valve (3), the hydrogen circulation pump (7), the air compressor (11), the second flow regulating valve (14), the third flow regulating valve (16), and the bypass flow regulating valve (18) are connected to the signal input terminal of the controller (21) via cables. The pressure sensor (8) is connected to the signal output terminal of the controller (21) via cables.

4. The energy transmission and supply system for a hydrogen-powered aircraft according to claim 1, characterized in that, The hydrogen circulation pump (7) is a variable frequency pump with adjustable speed.

5. The energy transmission and supply system for a hydrogen-powered aircraft according to claim 1, characterized in that, The heat exchange equipment for hydrogen engines (17) refers to the turbine blades of hydrogen engines.

6. A control method for an energy transmission and supply system of a hydrogen-powered aircraft, characterized in that, Specifically, the steps include the following: The controller (21) receives real-time status information of various equipment on the aircraft, the liquid hydrogen flow rate required for real-time heat dissipation of electronic equipment, hydraulic oil and lubricating oil on the computer, and the hydrogen supply flow rate required for the fuel cell (10) to generate electricity for the onboard electrical equipment; When the system is initially started, the controller (21) sends an opening command to the shut-off valve (2), the first flow regulating valve (3), and the third flow regulating valve (16), and sends a closing command to the second flow regulating valve (14) and the bypass flow regulating valve (18); the controller (21) sends a start signal to start the hydrogen circulation pump (7) and the air compressor (11). Determine the relationship between the liquid hydrogen flow rate required for cooling the electronic equipment, hydraulic oil, and lubricating oil and the hydrogen supply flow rate required by the fuel cell (10): When the liquid hydrogen flow rate required for cooling the electronic equipment, hydraulic oil, and lubricating oil is less than the hydrogen supply flow rate required by the fuel cell (10), close the bypass flow regulating valve (18), open and adjust the second flow regulating valve (14) to the valve opening degree corresponding to the difference between the two required flow rates; when the liquid hydrogen flow rate required for cooling the electronic equipment, hydraulic oil, and lubricating oil is greater than the hydrogen supply flow rate required by the fuel cell (10), close the second flow regulating valve (14), open and adjust the bypass flow regulating valve (18) to the valve opening degree corresponding to the difference between the two required flow rates; when the liquid hydrogen flow rate required for cooling the electronic equipment, hydraulic oil, and lubricating oil is equal to the hydrogen supply flow rate required by the fuel cell (10), close the second flow regulating valve (14) and the bypass flow regulating valve (18). The controller (21) receives pressure information from the pressure sensor (8) at its signal input terminal. When the hydrogen pressure monitored by the pressure sensor (8) is lower than the lower limit of the set value, the controller (21) sends an adjustment signal to the hydrogen circulation pump (7) at its signal output terminal to increase the speed of the hydrogen circulation pump (7). When the hydrogen pressure monitored by the pressure sensor (8) is higher than the upper limit of the set value, the controller (21) sends an adjustment signal to the hydrogen circulation pump (7) at its signal output terminal to decrease the speed of the hydrogen circulation pump (7). When the hydrogen pressure monitored by the pressure sensor (8) is within the range of the upper and lower limits of the set value, the controller (21) does not need to send an adjustment signal, and the speed of the hydrogen circulation pump (7) remains unchanged.

7. A hydrogen-powered aircraft, characterized in that, Including an energy transfer and supply system for a hydrogen-powered aircraft as described in any one of claims 1-5.

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