Hydrogen energy aviation fuel storage-supply system and method based on solid hydrogen storage

Abstract

The invention relates to the technical field of hydrogen energy aviation, and discloses a hydrogen energy aviation fuel storage-supply system and method based on solid hydrogen storage, and the hydrogen energy aviation fuel storage-supply system and method based on solid hydrogen storage are characterized in that the hydrogen release amount adjusting range of a hydrogen storage material is matched with the hydrogen fuel demand adjusting range of a power device by adjusting the hydrogen release catalytic reaction environment temperature of the solid hydrogen storage material; by adopting the pressure stabilizing device, the problem of flow and pressure fluctuation caused by hysteresis of hydrogen release adjustment is solved, and hydrogen release flow adjustment and engine throttling control can be carried out through the thrust rod.

Description

Technical Field

[0001] This invention relates to the field of hydrogen energy aviation technology, and discloses a hydrogen energy aviation fuel storage-supply system and method based on solid-state hydrogen storage. Background Technology

[0002] Solid-state hydrogen storage offers advantages such as high volumetric hydrogen density, easier achievement of required pressure and temperature conditions compared to high-pressure gaseous hydrogen and cryogenic liquid hydrogen, and lower risk of leakage and explosion due to the compound form of hydrogen. Among these, MgH2, as a solid-state hydrogen storage material, also boasts advantages such as low cost, optimizable cycle performance, and moderate thermodynamic stability (hydrogen release temperature approximately 300–400℃), demonstrating its potential in the development of hydrogen-powered aviation fuel storage and supply technologies. However, current hydrogen-powered aviation fuel supply technologies utilizing solid-state hydrogen storage face the following challenges: (1) The range of hydrogen release from hydrogen storage materials is mismatched with the range of hydrogen fuel demand from power plants. The hydrogen fuel demand of aero-engines varies significantly depending on the position of the aircraft in the mission profile, with a relative flow rate variation range of 10% to 100%, far exceeding the flow rate adjustment range of existing ground-based solid hydrogen storage fuel cells. The hydrogen release process of solid hydrogen storage materials is a chemical reaction process, which is limited by the complexity of the reaction system and the lag in temperature and concentration transfer, making it difficult to respond instantaneously to flow rate adjustment requirements.

[0003] (2) Due to the lag in the regulation of hydrogen release flow rate of solid hydrogen storage materials, fluctuations in hydrogen flow rate and pressure in fuel pipelines are easily caused. Due to the complexity of the hydrogen release reaction system of solid hydrogen storage materials and the lag in temperature and concentration transfer, fluctuations in flow rate and pressure are easily caused during the flow rate regulation process, which endangers the structural safety of pipelines and other components of the transmission system.

[0004] (3) Hydrogen release flow regulation and engine throttling control are difficult to adapt to the pilot's throttle lever operation habits, and it is difficult to regulate hydrogen release flow and control engine throttling through the "throttle lever". Summary of the Invention

[0005] The purpose of this invention is to provide a hydrogen energy aviation fuel storage and supply system and method based on solid-state hydrogen storage, which can match the hydrogen release range of the hydrogen storage material with the hydrogen fuel demand range of the power unit, avoid flow and pressure fluctuations caused by the lag in hydrogen release flow rate regulation, and also allow for hydrogen release flow rate regulation and engine throttling control via the thrust rod.

[0006] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows: A hydrogen fuel storage and supply system for aviation fuel based on solid-state hydrogen storage, used to supply hydrogen fuel to a power unit, comprising: Control device; A solid hydrogen storage device includes a hydrogen storage tank and a jacket structure located outside the hydrogen storage tank. The hydrogen storage tank is provided with a solid hydrogen storage material for generating hydrogen. The hydrogen storage tank supplies hydrogen to the fuel nozzle of the power unit through a hydrogen supply pipeline. A fuel flow control device includes a temperature-controlled tank storing a heat transfer medium, the temperature-controlled tank being connected to a jacket structure, the temperature-controlled tank being provided with a heating element and a radiator for adjusting the temperature of the heat transfer medium, and the heat transfer medium circulating between the temperature-controlled tank and the jacket structure to regulate the hydrogen release reaction temperature in the hydrogen storage tank; the heating element and the radiator are both electrically connected to the control device. A thrust rod angle sensor, which is electrically connected to the control device; A pressure stabilizing device is installed on the hydrogen supply pipeline between the hydrogen storage tank and the fuel nozzle of the power unit to buffer hydrogen; and the output end of the pressure stabilizing device is equipped with a pressure regulating valve. The hydrogen supply pipeline is also equipped with a hydrogen flow regulating valve and a hydrogen flow meter. The hydrogen flow regulating valve is used to regulate the hydrogen flow rate supplied to the fuel nozzle of the power unit, and the hydrogen flow meter is used to monitor the hydrogen flow rate supplied to the fuel nozzle of the power unit.

[0007] Furthermore, the jacket structure is provided with a heat transfer medium inlet and a heat transfer medium outlet communicating with the temperature control tank, and a heat transfer medium pump is provided at the heat transfer medium inlet and / or the heat transfer medium outlet.

[0008] Furthermore, the jacket structure is provided with a flow guiding mechanism to guide the heat transfer medium to flow along a preset path.

[0009] Furthermore, the hydrogen storage tank is also equipped with a heat transfer medium temperature sensor.

[0010] Furthermore, the temperature-controlled tank is equipped with a heat spreader for stirring the heat transfer medium inside the temperature-controlled tank.

[0011] Furthermore, the hydrogen supply pipeline is also equipped with a fuel supply shut-off valve and an overpressure relief valve. The fuel supply shut-off valve is located at the outlet of the solid hydrogen storage device, and the overpressure relief valve is located at the outlet end of the fuel supply shut-off valve.

[0012] A hydrogen-powered aviation fuel storage and supply method based on solid-state hydrogen storage, implemented using the aforementioned hydrogen-powered aviation fuel storage and supply system, comprising: Step 1: Determine the current thrust rod angle based on the feedback signal output by the thrust rod angle sensor; based on the current thrust rod angle, determine the target hydrogen demand flow rate of the engine, the target hydrogen release reaction temperature of the solid hydrogen storage device, and the target reaction pressure of the solid hydrogen storage device. Step 2: The fuel flow control device adjusts the temperature of the heat transfer medium to the target hydrogen release reaction temperature and introduces the heat transfer medium into the solid hydrogen storage device to regulate the hydrogen release reaction temperature in the hydrogen release reaction zone of the solid hydrogen storage device to the target hydrogen release reaction temperature; at the same time, it controls the pressure regulating valve of the pressure stabilizing device to adjust the hydrogen release reaction pressure in the solid hydrogen storage device to the target reaction pressure. Step 3: Real-time monitoring of the current hydrogen flow rate supplied to the power unit, as well as the current hydrogen release reaction temperature and current reaction pressure in the solid hydrogen storage device. If at least one of the parameters, namely the current hydrogen flow rate, the current hydrogen release reaction temperature, and the current reaction pressure, exceeds the corresponding preset safety threshold, a safety control strategy is triggered. Step 4: If the current hydrogen flow rate, current hydrogen release reaction temperature, and current reaction pressure do not exceed the corresponding preset safety thresholds, then compare the current hydrogen flow rate with the target hydrogen demand flow rate. If the deviation between the current hydrogen flow rate and the target hydrogen demand flow rate is less than the preset flow rate threshold, then it is considered that the current hydrogen flow rate supplied to the power unit matches the current thrust rod angle. Otherwise, repeat steps 1-3 until the current hydrogen flow rate matches the current thrust rod angle. Step 5: If the current hydrogen flow rate matches the current thrust rod angle, determine in real time whether the current thrust rod angle has changed based on the feedback signal output by the thrust rod angle sensor. If the current thrust rod angle has changed, repeat steps 1-4. Otherwise, repeat steps 3-4 at preset intervals.

[0013] Furthermore, the method by which the fuel flow control device adjusts the temperature of the heat transfer medium to the target hydrogen release reaction temperature is as follows: The temperature difference between the current hydrogen release reaction temperature and the target hydrogen release reaction temperature is determined based on the current hydrogen release reaction temperature and the target hydrogen release reaction temperature within the solid-state hydrogen storage device. The temperature of the current heat transfer medium is obtained, and the temperature of the heat transfer medium after temperature adjustment and the power of the fuel flow control device to adjust the temperature of the heat transfer medium are determined based on the temperature difference between the current hydrogen release reaction temperature and the target hydrogen release reaction temperature. Based on the power used to adjust the temperature of the heat transfer medium, determine the resistance value of the heating element required to heat the heat transfer medium, or determine the heat dissipation time of the radiator required to cool the heat transfer medium. The fuel flow control device heats or cools the heat transfer medium according to the resistance value of the heating element required to heat the heat transfer medium or the heat dissipation time of the radiator required to cool the heat transfer medium, so as to obtain a heat transfer medium with a temperature reaching the target hydrogen release reaction temperature.

[0014] Compared with the prior art, the beneficial effects of this invention are: This invention achieves a match between the hydrogen release rate adjustment range of the hydrogen storage material and the hydrogen fuel demand adjustment range of the power unit by adjusting the ambient temperature of the hydrogen release catalytic reaction environment of the solid hydrogen storage material. It solves the problem of flow and pressure fluctuation caused by the lag of hydrogen release adjustment by adopting a pressure stabilizing device. Moreover, it can also adjust the hydrogen release flow rate and control the engine throttling through the thrust rod. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of a hydrogen-powered aviation fuel storage and supply system based on solid-state hydrogen storage in the embodiment. Figure 2 This is a schematic diagram of the solid hydrogen storage device in the embodiment; Figure 3 This is a flowchart of a hydrogen-powered aviation fuel storage and supply method based on solid-state hydrogen storage, as shown in the embodiment.

[0016] In the diagram: 1-Solid-state hydrogen storage device, 11-Hydrogen storage tank, 12-Jacket structure, 121-Heat transfer medium pump, 122-Flow guiding mechanism, 13-Heat transfer medium temperature sensor, 2-Fuel flow control device, 21-Temperature control tank, 22-Heating element, 23-Radiator, 24-Evaporator, 3-Thrust rod angle sensor, 4-Pressure stabilizing device, 51-Hydrogen flow regulating valve, 52-Hydrogen flow meter, 53-Fuel supply shut-off valve, 54-Overpressure relief valve, 55-Hydrogen pipeline pressure indicator, 56-Hydrogen pipeline temperature indicator, 57-Hydrogen flow rate regulator, 58-Hydrogen manifold shut-off valve, 59-Hydrogen cross-transmission supply shut-off valve, 60-Relief valve. Detailed Implementation

[0017] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0018] Example See Figures 1-2 This embodiment provides a hydrogen-powered aviation fuel storage and supply system based on solid-state hydrogen storage, used to supply hydrogen fuel to a power unit, such as an aircraft engine. The hydrogen-powered aviation fuel storage and supply system includes: The control device may be a computer, PLC or other adapted controller.

[0019] Solid-state hydrogen storage device 1 includes a hydrogen storage tank 11 and a jacket structure 12 located outside the hydrogen storage tank 11. The hydrogen storage tank 11 is provided with a solid hydrogen storage material for generating hydrogen. Multiple solid-state hydrogen storage devices 1 can be set. In this embodiment, the solid hydrogen storage material is a hydrogen storage alloy based on MgH2. The solid hydrogen storage material is provided with a hydrogen release gas passage. The hydrogen released by the reaction flows through the hydrogen release gas passage to the hydrogen outlet of the hydrogen storage tank 11, and then flows into the hydrogen supply pipeline to supply hydrogen to the fuel nozzle of the power unit.

[0020] A fuel flow control device 2 includes a temperature-controlled tank 21 storing a heat transfer medium. The temperature-controlled tank 21 is connected to the jacket structure 12. The temperature-controlled tank 21 is equipped with a heating element 22 and a radiator 23 for adjusting the temperature of the heat transfer medium. The heat transfer medium circulates between the temperature-controlled tank 21 and the jacket structure 12 to regulate the hydrogen release reaction temperature within the hydrogen storage tank 11. Both the heating element 22 and the radiator 23 are electrically connected to the control device. The heating element 22 can be a heating resistor, and the radiator 23 can be an existing radiator 23 with heat dissipation fins. When the heat transfer medium needs to be heated, the heating power is determined by the control device by adjusting the resistance value of the heating resistor. When the heat transfer medium needs to be cooled, the heat dissipation power is also determined by the control device.

[0021] The thrust rod angle sensor 3 is electrically connected to the control device and is used to detect the angle of the aircraft thrust rod in real time and feed the detection signal back to the control device.

[0022] The pressure stabilizing device 4 is installed on the hydrogen supply pipeline between the hydrogen storage tank 11 and the fuel nozzle of the power unit. The pressure stabilizing device 4 includes a pressure stabilizing tank for buffering hydrogen; and the output end of the pressure stabilizing device 4 is provided with a pressure regulating valve.

[0023] The hydrogen supply pipeline is also equipped with a hydrogen flow regulating valve 51 and a hydrogen flow meter 52. The hydrogen flow regulating valve 51 is used to regulate the hydrogen flow rate supplied to the fuel nozzle of the power unit, and the hydrogen flow meter is used to monitor the hydrogen flow rate supplied to the fuel nozzle of the power unit. The hydrogen flow regulating valve 51 adjusts the valve opening based on the signal output by the hydrogen fuel flow meter using a PID control method, thereby realizing the flow regulation of the hydrogen supply pipeline.

[0024] This embodiment uses a control device as the "brain" of the entire system. Based on the signal fed back by the thrust rod angle sensor 3, it accurately determines the fuel demand of the power unit and adjusts the operating status of the fuel flow control device 2 in real time. The fuel flow control device 2 regulates the temperature of the heat transfer medium inside the temperature-controlled tank 21 to adjust the hydrogen release reaction temperature in the hydrogen release reaction zone inside the hydrogen storage tank 11, thereby regulating the hydrogen release rate. In the hydrogen supply pipeline, a pressure stabilizing device 4 is used to suppress flow and pressure fluctuations in the pipeline, ensuring stable operation of the hydrogen supply pipeline. Furthermore, the cooperation of the hydrogen flow regulating valve 51 and the hydrogen flow meter 52 enables precise adjustment and real-time monitoring of the hydrogen flow rate supplied to the fuel nozzle of the power unit, meeting the stringent requirements of power units such as aero engines for hydrogen fuel. This embodiment achieves matching between the hydrogen release rate adjustment range of the hydrogen storage material and the hydrogen fuel demand adjustment range of the power unit by adjusting the temperature of the hydrogen release catalytic reaction environment of the solid hydrogen storage material. The use of the pressure stabilizing device 4 solves the problem of flow and pressure fluctuations caused by the lag in hydrogen release regulation. In addition, the thrust rod is used to regulate the hydrogen release flow rate and control the engine throttling.

[0025] In some embodiments, the jacket structure 12 is provided with a heat transfer medium inlet and a heat transfer medium outlet communicating with the temperature-controlled tank 21. A heat transfer medium pump 121 is provided at the heat transfer medium inlet and / or outlet to pump the heat transfer medium into and / or out of the hydrogen storage tank 11, driving the heat transfer medium to circulate between the hydrogen storage tank 11 and the temperature-controlled tank 21. A flow guiding mechanism 122 is provided in the non-hydrogen release reaction zone within the hydrogen storage tank 11. The flow guiding mechanism 122 guides the heat transfer medium to flow along a preset path to efficiently and uniformly regulate the temperature of the hydrogen release reaction zone. In this embodiment, the hydrogen storage tank 11 can be a tank with a jacket structure 12. Solid hydrogen storage material is placed inside the hydrogen storage tank 11 as the hydrogen release reaction zone. The jacket of the hydrogen storage tank 11 communicates with the temperature-controlled tank 21 and is used for heat transfer medium flow. A flow guiding mechanism 122 is provided within the jacket. The flow guiding mechanism 122 can be several guide plates to... Figure 2 As shown, the flow channel inside the jacket is S-shaped, so that when the heat transfer medium flows inside the jacket, there is enough time for heat exchange between the heat transfer medium and the hydrogen release reaction zone, thus ensuring effective regulation of the reaction temperature in the hydrogen release reaction zone.

[0026] In some embodiments, the hydrogen storage tank 11 is further equipped with a heat transfer medium temperature sensor 13, which monitors the temperature inside the heat transfer medium of the hydrogen storage tank 11 in real time to prevent overheating. Simultaneously, the hydrogen storage tank 11 is also equipped with a reaction temperature sensor and a reaction pressure sensor. The reaction temperature sensor detects the reaction temperature during the reaction of the solid hydrogen storage material, and the reaction pressure sensor detects the pressure inside the hydrogen storage tank 11.

[0027] In some embodiments, a heat spreader 24 is provided inside the temperature-controlled tank 21 for stirring the heat transfer medium inside the temperature-controlled tank 21. The heat spreader 24 can be a motor-driven stirrer installed inside the temperature-controlled tank 21. When heating or cooling the heat transfer medium, the stirrer agitates the heat transfer medium, causing it to circulate within the temperature-controlled tank 21, thereby achieving the purpose of uniform heating or cooling of the heat transfer medium as a whole.

[0028] In some embodiments, the hydrogen supply pipeline is further equipped with a fuel supply shut-off valve 53 and an overpressure relief valve 54. The fuel supply shut-off valve 53 is located at the outlet of the solid hydrogen storage device 1, and the overpressure relief valve 54 is located at the outlet end of the fuel supply shut-off valve 53. During normal hydrogen supply, the fuel supply shut-off valve 53 is open, and the hydrogen gas output from the hydrogen storage tank 11 flows into the hydrogen supply pipeline. When the hydrogen supply pipeline malfunctions or hydrogen supply is not required, the fuel supply shut-off valve 53 is closed to cut off the hydrogen supply. When the outlet pressure of the hydrogen storage tank 11 exceeds the preset maximum pressure, the overpressure relief valve 54 is opened to release hydrogen gas to protect the safety of the hydrogen supply pipeline.

[0029] In some embodiments, the hydrogen supply line is further provided with a hydrogen supply line pressure indicator 55 for detecting the hydrogen pressure in the hydrogen supply line, and a hydrogen supply line temperature indicator 56 for detecting the hydrogen temperature in the hydrogen supply line. A hydrogen flow rate regulator 57 is located downstream of the hydrogen flow regulating valve 51 and is used to regulate the hydrogen flow rate.

[0030] The working principle of this hydrogen-powered aviation fuel storage and supply system is as follows: The heat transfer medium pump 121 in the solid hydrogen storage device 1 drives the heat transfer medium in the temperature-controlled tank 21 to circulate between the hydrogen storage tank 11 and the temperature-controlled tank 21. When the feedback signal from the thrust rod angle sensor 3 indicates a need to increase the hydrogen flow rate supplied to the power unit, the control device determines the target hydrogen flow rate required by the engine, the target hydrogen release reaction temperature of the solid hydrogen storage device 1, and the target reaction pressure of the solid hydrogen storage device 1 based on the feedback signal from the thrust rod angle sensor 3. Then, based on the current hydrogen release reaction temperature and the target hydrogen release reaction temperature in the solid hydrogen storage device 1, the temperature difference between the current hydrogen release reaction temperature and the target hydrogen release reaction temperature is determined. Then, based on the current temperature of the heat transfer medium and the temperature difference between the current hydrogen release reaction temperature and the target hydrogen release reaction temperature, the temperature of the heat transfer medium after heating is determined. Then, the heating power of the heating heat transfer medium is determined, and then the resistance value of the heating resistor is determined. Then, the fuel flow control device 2 heats the heat transfer medium. As the temperature of the heat transfer medium continuously rises and approaches the target hydrogen release reaction temperature, the reaction environment temperature of the solid hydrogen storage material inside the hydrogen storage tank 11 also continuously rises and approaches the target hydrogen release reaction temperature. The hydrogen release rate from the hydrogen storage tank 11 continuously increases. Simultaneously, in conjunction with the pressure regulating valve of the pressure stabilizing device 4, the hydrogen pressure in the pipeline from the pressure stabilizing device 4 to the hydrogen storage tank 11 and the reaction pressure inside the hydrogen storage tank 11 reach the target reaction pressure. Then, based on the current hydrogen flow rate supplied to the power unit as fed back by the hydrogen fuel flow meter, the control device, according to the target hydrogen demand flow rate and the current hydrogen flow rate supplied to the power unit, adjusts the opening of the hydrogen flow regulating valve 51 through PID control, ensuring that the hydrogen flow rate output by the hydrogen flow regulating valve 51 to the power unit reaches the target hydrogen demand flow rate. Simultaneously, the hydrogen flow rate output to the power unit can also be adjusted by controlling the hydrogen flow rate regulator 57. When it is determined, based on the feedback signal from the thrust rod angle sensor 3, that the hydrogen flow rate supplied to the power unit needs to be reduced, the working principle is the same as described above, except that the fuel flow control device 2 dissipates heat to cool the heat transfer medium.

[0031] It should be noted that the power unit at the end of the hydrogen supply pipeline can be configured as two lines, namely a first branch and a second branch. The first branch is equipped with a hydrogen manifold shut-off valve 58 to control the on / off of the hydrogen supply to the first branch, and the second branch is equipped with a hydrogen cross-transmission supply shut-off valve 59 to control the on / off of the hydrogen supply to the second branch. Each branch is connected to an engine, so that the entire system can be adapted to the hydrogen supply of multiple engines.

[0032] Based on the same inventive concept, such as Figure 3 This embodiment also provides a hydrogen-powered aviation fuel storage and supply method based on solid-state hydrogen storage, implemented based on the aforementioned hydrogen-powered aviation fuel storage and supply system, which includes: Step 1: The thrust rod angle sensor 3 detects the angle of the thrust rod in real time. Based on the feedback signal output by the thrust rod angle sensor 3, the current angle of the thrust rod is determined. Based on the current angle of the thrust rod, the target hydrogen flow rate required by the engine, the target hydrogen release reaction temperature of the solid hydrogen storage device 1, and the target reaction pressure of the solid hydrogen storage device 1 are determined. The target reaction pressure refers to the pressure inside the solid hydrogen storage tank 11.

[0033] Step 2: The fuel flow control device 2 adjusts the temperature of the heat transfer medium to the target hydrogen release reaction temperature, and introduces the heat transfer medium into the solid hydrogen storage device 1 to regulate the hydrogen release reaction temperature in the hydrogen release reaction zone of the solid hydrogen storage device 1 to the target hydrogen release reaction temperature; at the same time, it controls the pressure regulating valve of the pressure stabilizing device 4 to adjust the hydrogen release reaction pressure in the solid hydrogen storage device 1 to the target reaction pressure.

[0034] Specifically, the method by which the fuel flow control device 2 adjusts the temperature of the heat transfer medium to the target hydrogen release reaction temperature is as follows: M1: Determine the temperature difference between the current hydrogen release reaction temperature and the target hydrogen release reaction temperature based on the current hydrogen release reaction temperature and the target hydrogen release reaction temperature in the solid hydrogen storage device 1.

[0035] M2: Obtain the current temperature of the heat transfer medium, and determine the temperature of the heat transfer medium after temperature adjustment and the power of the fuel flow control device 2 to adjust the temperature of the heat transfer medium based on the temperature difference between the current hydrogen release reaction temperature and the target hydrogen release reaction temperature. If the heat transfer medium needs to be heated, the power is the heating power; if the heat transfer medium needs to be cooled, the power is the heat dissipation power.

[0036] M3: Determine the resistance value of the heating element 22 required to heat the heat transfer medium based on the power used to adjust the temperature of the heat transfer medium, or determine the heat dissipation time of the radiator 23 required to cool the heat transfer medium.

[0037] M4: The fuel flow control device 2 heats or cools the heat transfer medium according to the resistance value of the heating element 22 required to heat the heat transfer medium or the heat dissipation time of the radiator 23 required to cool the heat transfer medium, so as to obtain a heat transfer medium with a temperature reaching the target hydrogen release reaction temperature.

[0038] In actual operation, the heat transfer medium circulates between the temperature control tank 21 and the hydrogen storage tank 11. When it is heated or cooled to the target hydrogen release reaction temperature, the reaction temperature of the solid hydrogen storage material in the hydrogen storage tank 11 also changes as the temperature of the heat transfer medium changes. This adjusts the reaction temperature of the solid hydrogen storage material in the hydrogen storage tank 11, thereby adjusting the hydrogen release flow rate of the solid hydrogen storage device 1 and providing a basis for adjusting the hydrogen flow rate supplied to the engine.

[0039] Step 3: Real-time monitoring of the current hydrogen flow rate supplied to the power unit, and the current hydrogen release reaction temperature and current reaction pressure within the solid-state hydrogen storage device 1. If at least one of the following parameters exceeds a corresponding preset safety threshold, a safety control strategy is triggered: This could involve lowering the temperature of the heat transfer medium to reduce the hydrogen release reaction temperature and thus the hydrogen release rate; opening the vent valve 60 on the hydrogen supply pipeline to reduce the current hydrogen flow rate supplied to the power unit; or opening the overpressure vent valve 54 to prevent overpressure within the hydrogen storage tank 11. The current reaction pressure refers to the current pressure within the hydrogen storage tank 11. It should be noted that the preset safety thresholds for the current hydrogen flow rate supplied to the power unit, the current hydrogen release reaction temperature within the solid-state hydrogen storage device 1, and the current reaction pressure are all preset thresholds, set by those skilled in the art based on experience or needs.

[0040] Step 4: If the current hydrogen flow rate supplied to the power unit, the current hydrogen release reaction temperature in the solid hydrogen storage device 1, and the current reaction pressure do not exceed the corresponding preset safety thresholds, then the current hydrogen flow rate is compared with the target hydrogen demand flow rate. If the deviation between the current hydrogen flow rate and the target hydrogen demand flow rate is less than the preset flow rate threshold, then it is considered that the current hydrogen flow rate supplied to the power unit matches the current thrust rod angle. Otherwise, repeat steps 1-3 until the current hydrogen flow rate matches the current thrust rod angle, thereby achieving hydrogen fuel flow rate regulation. Step 5: If the current hydrogen flow rate supplied to the power unit matches the current thrust rod angle, determine in real time whether the current thrust rod angle has changed based on the feedback signal output by the thrust rod angle sensor 3. If the current thrust rod angle has changed, repeat steps 1-4; otherwise, repeat steps 3-4 at preset intervals.

[0041] This invention achieves a match between the hydrogen release range of the hydrogen storage material and the hydrogen fuel demand range of the power unit by adjusting the ambient temperature of the hydrogen release catalytic reaction environment of the solid hydrogen storage material. The use of a pressure stabilizing device 4 solves the problem of flow and pressure fluctuations caused by the lag in hydrogen release regulation. Furthermore, the hydrogen release flow rate can be adjusted and the engine throttling can be controlled by the thrust rod.

[0042] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A hydrogen fuel storage and supply system for aviation fuel based on solid-state hydrogen storage, used to supply hydrogen fuel to a power unit, characterized in that, include: Control device; Solid hydrogen storage device (1), the solid hydrogen storage device (1) includes a hydrogen storage tank (11) and a jacket structure (12) located outside the hydrogen storage tank (11). The hydrogen storage tank (11) is provided with solid hydrogen storage material for generating hydrogen. The hydrogen storage tank (11) supplies hydrogen to the fuel nozzle of the power unit through a hydrogen supply pipeline. A fuel flow control device (2) includes a temperature-controlled tank (21) storing a heat transfer medium. The temperature-controlled tank (21) is connected to the jacket structure (12). The temperature-controlled tank (21) is provided with a heating element (22) and a radiator (23) for adjusting the temperature of the heat transfer medium. The heat transfer medium circulates between the temperature-controlled tank (21) and the jacket structure (12) to regulate the hydrogen release reaction temperature in the hydrogen storage tank (11). The heating element (22) and the radiator (23) are both electrically connected to the control device. A thrust rod angle sensor (3) is electrically connected to the control device; A pressure stabilizing device (4) is installed on the hydrogen supply pipeline between the hydrogen storage tank (11) and the fuel nozzle of the power unit to buffer hydrogen; and a pressure regulating valve is provided at the output end of the pressure stabilizing device (4). The hydrogen supply pipeline is also equipped with a hydrogen flow regulating valve (51) and a hydrogen flow meter (52). The hydrogen flow regulating valve (51) is used to regulate the hydrogen flow rate supplied to the fuel nozzle of the power unit, and the hydrogen flow meter (52) is used to monitor the hydrogen flow rate supplied to the fuel nozzle of the power unit.

2. The hydrogen-powered aviation fuel storage and supply system according to claim 1, characterized in that, The jacket structure (12) is provided with a heat transfer medium inlet and a heat transfer medium outlet that are connected to the temperature control tank (21), and a heat transfer medium pump (121) is provided at the heat transfer medium inlet and / or the heat transfer medium outlet.

3. The hydrogen-powered aviation fuel storage and supply system according to claim 2, characterized in that, The jacket structure (12) is provided with a flow guiding mechanism (122) for guiding the heat transfer medium to flow along a preset path.

4. The hydrogen-powered aviation fuel storage and supply system according to claim 2, characterized in that, The hydrogen storage tank (11) is also equipped with a heat transfer medium temperature sensor (13).

5. The hydrogen-powered aviation fuel storage and supply system according to claim 1, characterized in that, The temperature-controlled tank (21) is equipped with a heat spreader (24) for stirring the heat transfer medium inside the temperature-controlled tank (21).

6. The hydrogen-powered aviation fuel storage and supply system according to claim 1, characterized in that, The hydrogen supply pipeline is also equipped with a fuel supply shut-off valve (53) and an overpressure relief valve (54). The fuel supply shut-off valve (53) is located at the outlet of the solid hydrogen storage device (1), and the overpressure relief valve (54) is located at the outlet end of the fuel supply shut-off valve (53).

7. A method for storing and supplying hydrogen-powered aviation fuel based on solid-state hydrogen storage, implemented using the hydrogen-powered aviation fuel storage and supply system described in any one of claims 1-6, characterized in that, include: Step 1: Determine the current angle of the thrust rod based on the feedback signal output by the thrust rod angle sensor (3); and determine the target flow rate of hydrogen demand of the engine, the target hydrogen release reaction temperature of the solid hydrogen storage device (1), and the target reaction pressure of the solid hydrogen storage device (1) based on the current angle of the thrust rod. Step 2: The fuel flow control device (2) adjusts the temperature of the heat transfer medium to the target hydrogen release reaction temperature and introduces the heat transfer medium into the solid hydrogen storage device (1) to regulate the hydrogen release reaction temperature in the hydrogen release reaction zone of the solid hydrogen storage device (1) to the target hydrogen release reaction temperature; at the same time, it controls the pressure regulating valve of the pressure stabilizing device (4) to adjust the hydrogen release reaction pressure in the solid hydrogen storage device (1) to the target reaction pressure; Step 3: Real-time detection of the current hydrogen flow rate supplied to the power unit, as well as the current hydrogen release reaction temperature and current reaction pressure in the solid hydrogen storage device (1). If at least one of the parameters of the current hydrogen flow rate, current hydrogen release reaction temperature, and current reaction pressure exceeds the corresponding preset safety threshold, a safety control strategy is triggered. Step 4: If the current hydrogen flow rate, current hydrogen release reaction temperature, and current reaction pressure do not exceed the corresponding preset safety thresholds, then compare the current hydrogen flow rate with the target hydrogen demand flow rate. If the deviation between the current hydrogen flow rate and the target hydrogen demand flow rate is less than the preset flow rate threshold, then it is considered that the current hydrogen flow rate supplied to the power unit matches the current thrust rod angle. Otherwise, repeat steps 1-3 until the current hydrogen flow rate matches the current thrust rod angle. Step 5: If the current hydrogen flow rate matches the current thrust rod angle, determine in real time whether the current thrust rod angle has changed based on the feedback signal output by the thrust rod angle sensor (3). If the current thrust rod angle has changed, repeat steps 1-4. Otherwise, repeat steps 3-4 at preset intervals.

8. The hydrogen-powered aviation fuel storage and supply method according to claim 7, characterized in that, The method by which the fuel flow control device (2) adjusts the temperature of the heat transfer medium to the target hydrogen release reaction temperature is as follows: Based on the current hydrogen release reaction temperature and the target hydrogen release reaction temperature in the solid hydrogen storage device (1), determine the temperature difference between the current hydrogen release reaction temperature and the target hydrogen release reaction temperature; The temperature of the current heat transfer medium is obtained, and the temperature of the heat transfer medium after temperature adjustment and the power of the fuel flow control device (2) to adjust the temperature of the heat transfer medium are determined based on the temperature difference between the current hydrogen release reaction temperature and the target hydrogen release reaction temperature. Based on the power used to adjust the temperature of the heat transfer medium, determine the resistance value of the heating element (22) required to heat the heat transfer medium, or determine the heat dissipation time of the radiator (23) required to cool the heat transfer medium. The fuel flow control device (2) heats or cools the heat transfer medium according to the resistance value of the heating element (22) required to heat the heat transfer medium or the heat dissipation time of the radiator (23) required to cool the heat transfer medium, so as to obtain a heat transfer medium with a temperature reaching the target hydrogen release reaction temperature.

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