Liquid hydrogen power aircraft

Abstract

The invention relates to a liquid hydrogen power aircraft, comprising: a liquid hydrogen storage system comprising a liquid hydrogen storage tank for storing liquid hydrogen, a liquid hydrogen pump arranged in the liquid hydrogen storage tank and used for conveying the liquid hydrogen to a liquid hydrogen vaporization device; the liquid hydrogen vaporization device is used for converting liquid hydrogen into normal-temperature high-pressure hydrogen; the fuel conveying and control system is used for conveying the normal-temperature high-pressure hydrogen to the combustion system; the combustion system comprises an engine which is provided with a combustion chamber, and combustion of hydrogen is conducted in the combustion chamber to generate thrust; heat generated during combustion is obtained through an air entraining pipe or an exhaust nozzle to serve as a heat source of the liquid hydrogen vaporization device; and under the action of the heat source, the liquid hydrogen is vaporized after passing through the liquid hydrogen vaporizing device and reaches a combustible state. The liquid hydrogen power system can be used for an aircraft in which liquid hydrogen fuel generates power through combustion, the number of needed devices is small, the overall weight of the liquid hydrogen power system is low, and the reliability of the overall framework of the liquid hydrogen power system is improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft design, in particular to a liquid hydrogen powered aircraft. Background Art

[0002] In response to the global trend of carbon emission reduction in civil aviation, ICAO has formulated mandatory carbon emission standards. Hydrogen energy, as a renewable clean energy and pollution-free, is the most likely power source for future new energy aircraft.

[0003] At present, regional airliners and small aircraft or aircraft mostly use hydrogen-oxygen fuel cells as energy sources, but the power requirements of trunk airliners or large aircraft are relatively large, and the power density of hydrogen-oxygen fuel cells is low, making it difficult to meet this type of power requirements. For this reason, hydrogen fuel (referring to gaseous hydrogen, i.e. hydrogen) needs to be transported to the engine combustion chamber for combustion, thereby outputting a larger power. However, the density of liquid hydrogen is more than 800 times that of gaseous hydrogen under standard conditions. In order to reduce the volume of the aircraft fuel tank, the hydrogen fuel needs to be cooled to below -253°C for liquefied storage.

[0004] In the process of the liquid hydrogen pump transporting liquid hydrogen from the liquid hydrogen storage tank to the engine, the processes involved are the control, vaporization, voltage stabilization, and flow regulation of liquid hydrogen fuel. Therefore, a reliable and lightweight liquid hydrogen power architecture is the focus of research on aircraft of the mainline passenger aircraft and above. When this type of aircraft is working, the demand for liquid hydrogen flow is large, which is difficult to achieve through conventional liquid hydrogen evaporation or gas pressurization. A liquid hydrogen pump needs to be set up to achieve a large flow of liquid hydrogen supply. If the liquid hydrogen pump is arranged outside the liquid hydrogen storage tank, a liquid hydrogen tank needs to be separately configured for the liquid hydrogen pump to ensure that the liquid hydrogen pump is immersed in liquid hydrogen, which causes a sharp increase in the weight of the liquid hydrogen power system.

[0005] Because the liquid hydrogen in the liquid hydrogen storage tank is consumed quickly, the liquid hydrogen storage tank needs to be pressurized, otherwise it will cause negative pressure, making it difficult to pump out the liquid hydrogen or damage the liquid hydrogen storage tank. In order to ensure the safety of liquid hydrogen, air cannot be passed into the liquid hydrogen storage tank, otherwise it is easy to explode when using hydrogen fuel. In addition, the temperature of the liquid hydrogen storage tank is extremely low. When general gases are passed into the liquid hydrogen storage tank, they are easily solidified due to the ultra-low temperature, thus failing to increase the pressure.

[0006] The information disclosed in this background technology section is only intended to deepen the understanding of the overall background technology of the present invention, and should not be regarded as acknowledging or suggesting in any form that the information constitutes the prior art already known to those skilled in the art. Summary of the invention

[0007] In view of the defects existing in the prior art, the purpose of the present invention is to provide a liquid hydrogen powered aircraft, mainly to solve the problems of liquid hydrogen power system architecture design, liquid hydrogen storage tank pressure stabilization design, liquid hydrogen power system control design, liquid hydrogen power system function realization, reducing the weight of the liquid hydrogen power system, and solving the heat source of the liquid hydrogen vaporization device.

[0008] In order to achieve the above purpose, the technical solution adopted by the present invention is:

[0009] A liquid hydrogen powered aircraft, characterized by comprising:

[0010] A liquid hydrogen storage system, comprising a liquid hydrogen storage tank 100 for storing liquid hydrogen, wherein a liquid hydrogen pump 101 is arranged in the liquid hydrogen storage tank 100, and the liquid hydrogen pump 101 is used to transport the liquid hydrogen to the liquid hydrogen vaporization device 600;

[0011] Liquid hydrogen vaporization device 600, used to convert liquid hydrogen into normal temperature and high pressure hydrogen;

[0012] Fuel delivery and control system, used to deliver room temperature and high pressure hydrogen to the combustion system;

[0013] The combustion system includes an engine 800, which has a combustion chamber 801, in which hydrogen is burned to generate thrust; the heat generated during combustion is obtained through the bleed air or tail nozzle 802 as a heat source for the liquid hydrogen vaporization device 600; under the action of the heat source, the liquid hydrogen is vaporized after passing through the liquid hydrogen vaporization device 600 and reaches a combustible state.

[0014] On the basis of the above technical solution, a liquid hydrogen filling port is provided on the top of the liquid hydrogen storage tank 100, and a filling pipeline 900 is connected to the liquid hydrogen filling port for filling liquid hydrogen into the liquid hydrogen storage tank 100;

[0015] The filling pipeline 900 is provided with a regulating valve.

[0016] On the basis of the above technical solution, the liquid hydrogen storage tank 100 is provided with a venting pipeline 300 for safely discharging liquid hydrogen when necessary to prevent accidents;

[0017] The liquid hydrogen storage tank 100 is connected to the venting pipeline 300 through a first connecting pipeline, and a safety valve 301 is provided on the first connecting pipeline;

[0018] The vent line 300 is connected to the atmosphere 304 after passing through the flame arrester 303 .

[0019] On the basis of the above technical solution, a pressure stabilizing pipeline 200 is provided between the liquid hydrogen vaporizing device 600 and the liquid hydrogen storage tank 100 for controlling the pressure of the liquid hydrogen storage tank 100;

[0020] The pressure stabilizing pipeline 200 is connected to the second regulating valve 201, and the second regulating valve 201 is directly connected to the liquid hydrogen storage tank 100 through the second connecting pipeline. The second regulating valve 201 is also connected to the vent valve 302 through the third connecting pipeline, and the vent valve 302 is connected to the vent pipeline 300 between the safety valve 301 and the flame arrester 303.

[0021] On the basis of the above technical solution, the liquid hydrogen pump 101 is connected to the liquid hydrogen vaporization device 600 through a fourth connecting pipeline;

[0022] The fourth connecting pipeline is provided with a first regulating valve 102 .

[0023] On the basis of the above technical solution, a fuel delivery pipeline is provided between the liquid hydrogen vaporization device 600 and the engine 800;

[0024] The fuel delivery pipeline is provided with a first pressure and temperature sensor 501, a hydrogen fuel controller 400, a second pressure and temperature sensor 502 and a one-way valve 700 in sequence;

[0025] The hydrogen fuel controller 400 includes a filter 401 and a flow regulating valve 402, and is used to accurately control the flow and pressure of hydrogen.

[0026] On the basis of the above technical solution, the liquid hydrogen storage tank 100 is provided with a pressure and temperature monitoring system for safety monitoring;

[0027] The pressure and temperature monitoring system includes: a liquid level sensor L, a temperature sensor T and a pressure sensor P arranged in the liquid hydrogen storage tank 100, and is used to monitor the state in the liquid hydrogen storage tank 100.

[0028] On the basis of the above technical solution, when the pressure in the liquid hydrogen storage tank 100 exceeds the normal working range, the safety valve 301 automatically opens as a pressure switch, and automatically closes when the pressure in the liquid hydrogen storage tank 100 returns to the normal working range, thereby maintaining the pressure of the liquid hydrogen storage tank 100 stable.

[0029] The liquid hydrogen powered aircraft described in the present invention has the following beneficial effects:

[0030] The liquid hydrogen powered aircraft architecture scheme has a low weight: ① The liquid hydrogen pump 101 is arranged in the liquid hydrogen storage tank 100, reducing the small storage tank that is added by arranging the liquid hydrogen pump separately; ② Normal temperature and high pressure hydrogen is quoted from the liquid hydrogen vaporization device 600, which reduces the gas consumption for pressurizing the liquid hydrogen storage tank 100, and there is no need to set up special pressure stabilizing and heating equipment.

[0031] The architecture of this liquid hydrogen powered aircraft has good reliability: ① Flame arrester 303 and one-way valve 700 are arranged on the normal temperature and high pressure hydrogen transmission pipeline to prevent the normal temperature and high pressure hydrogen from flowing back or tempering; ② Normal temperature and high pressure hydrogen is used after the liquid hydrogen vaporization device 600 to stabilize the pressure in the liquid hydrogen storage tank 100, reducing additional heat sources and pressure stabilizing heating equipment, so that the equipment of this architecture is reduced, thereby relatively improving the reliability of the system.

[0032] The liquid hydrogen powered aircraft described in the present invention can be used for aircraft that generate power through combustion of liquid hydrogen fuel. Less equipment is required, the overall weight of the liquid hydrogen power system is low, and the reliability of the overall architecture of the liquid hydrogen power system is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The present invention has the following accompanying drawings:

[0034] The accompanying drawings are used to better understand the present invention and do not constitute an improper limitation of the present invention.

[0035] Figure 1 System architecture diagram of embodiment 1 of a liquid hydrogen powered aircraft described in the present invention. DETAILED DESCRIPTION

[0036] The present invention is further described in detail below in conjunction with the accompanying drawings. The detailed description is an explanation made in conjunction with the exemplary embodiments of the present invention, including various details of the embodiments of the present invention to facilitate understanding, which should be considered as merely exemplary. Therefore, it should be recognized by those skilled in the art that various changes and modifications can be made to the embodiments described herein without departing from the scope and spirit of the present invention. Similarly, for the sake of clarity and conciseness, the description of well-known functions and structures is omitted in the following description.

[0037] The current scheme of generating power through liquid hydrogen turbines does not take into account the pressure stabilization of liquid hydrogen storage tanks, the placement of liquid hydrogen pumps, and the heat source of liquid hydrogen vaporization devices. Figure 1 As shown, the present invention provides a liquid hydrogen powered aircraft, comprising:

[0038] A liquid hydrogen storage system, comprising a liquid hydrogen storage tank 100 for storing liquid hydrogen, wherein a liquid hydrogen pump 101 is arranged in the liquid hydrogen storage tank 100, and the liquid hydrogen pump 101 is used to transport the liquid hydrogen to the liquid hydrogen vaporization device 600;

[0039] Liquid hydrogen vaporization device 600, used to convert liquid hydrogen into normal temperature and high pressure hydrogen;

[0040] Fuel delivery and control system, used to deliver room temperature and high pressure hydrogen to the combustion system;

[0041] The combustion system includes an engine 800, which has a combustion chamber 801, in which hydrogen is burned to generate thrust; the heat generated during combustion is obtained through the bleed air or tail nozzle 802 as a heat source for the liquid hydrogen vaporization device 600; under the action of the heat source, the liquid hydrogen is vaporized after passing through the liquid hydrogen vaporization device 600 and reaches a combustible state; the engine 800 can optionally use a turbine.

[0042] On the basis of the above technical solution, a liquid hydrogen filling port is provided on the top of the liquid hydrogen storage tank 100, and a filling pipeline 900 is connected to the liquid hydrogen filling port for filling liquid hydrogen into the liquid hydrogen storage tank 100;

[0043] The filling pipeline 900 is provided with a regulating valve.

[0044] On the basis of the above technical solution, the liquid hydrogen storage tank 100 is provided with a venting pipeline 300 for safely discharging liquid hydrogen when necessary to prevent accidents;

[0045] The liquid hydrogen storage tank 100 is connected to the venting pipeline 300 through a first connecting pipeline, and a safety valve 301 is provided on the first connecting pipeline; the safety valve 301 can be a cryogenic mechanical valve;

[0046] The venting pipeline 300 is connected to the atmosphere 304 after passing through the flame arrester 303 .

[0047] On the basis of the above technical solution, a pressure stabilizing pipeline 200 is provided between the liquid hydrogen vaporizing device 600 and the liquid hydrogen storage tank 100 for controlling the pressure of the liquid hydrogen storage tank 100;

[0048] The pressure stabilizing pipeline 200 is connected to the second regulating valve 201, and the second regulating valve 201 is directly connected to the liquid hydrogen storage tank 100 through the second connecting pipeline. The second regulating valve 201 is also connected to the vent valve 302 through the third connecting pipeline, and the vent valve 302 is connected to the vent pipeline 300 between the safety valve 301 and the flame arrester 303; the vent valve 302 can select a low-temperature solenoid valve.

[0049] When the pressure in the liquid hydrogen storage tank 100 is lower than the normal range, the normal temperature and high pressure hydrogen gas passing through the liquid hydrogen vaporization device 600 replenishes the pressure in the liquid hydrogen storage tank 100 through the pressure stabilizing pipeline 200 .

[0050] The second regulating valve 201 plays the role of on-off control and flow regulation.

[0051] On the basis of the above technical solution, the liquid hydrogen pump 101 is connected to the liquid hydrogen vaporization device 600 through a fourth connecting pipeline;

[0052] The fourth connecting pipeline is provided with a first regulating valve 102 .

[0053] On the basis of the above technical solution, a fuel delivery pipeline is provided between the liquid hydrogen vaporization device 600 and the engine 800;

[0054] The fuel delivery pipeline is provided with a first pressure and temperature sensor 501, a hydrogen fuel controller 400, a second pressure and temperature sensor 502 and a one-way valve 700 in sequence;

[0055] The hydrogen fuel controller 400 includes a filter 401 and a flow regulating valve 402, and is used to accurately control the flow and pressure of hydrogen.

[0056] Normal temperature and high pressure hydrogen is delivered to the engine through the hydrogen fuel controller 400, the one-way valve 700, etc., which is equivalent to realizing the function of throttle adjustment. Since hydrogen is the smallest molecule, the flow and pressure control are difficult to be accurately controlled by the liquid hydrogen pump. Therefore, the hydrogen fuel controller 400 is arranged after the liquid hydrogen vaporization device 600. The flow regulating valve 402 on the hydrogen fuel controller 400 can accurately control the hydrogen flow. The one-way valve 700 is arranged after the hydrogen fuel controller 400 to prevent the backflow of hydrogen fuel. The first pressure and temperature sensor 501 is also arranged after the liquid hydrogen vaporization device 600 to ensure that the state of liquid hydrogen during the transportation process meets the requirements.

[0057] On the basis of the above technical solution, the liquid hydrogen storage tank 100 is provided with a pressure and temperature monitoring system for safety monitoring;

[0058] The pressure and temperature monitoring system includes: a liquid level sensor L, a temperature sensor T and a pressure sensor P arranged in the liquid hydrogen storage tank 100, and is used to monitor the state in the liquid hydrogen storage tank 100.

[0059] On the basis of the above technical solution, when the pressure in the liquid hydrogen storage tank 100 exceeds the normal working range, the safety valve 301 automatically opens as a pressure switch, and automatically closes when the pressure in the liquid hydrogen storage tank 100 returns to the normal working range, thereby maintaining the pressure of the liquid hydrogen storage tank 100 stable.

[0060] The present invention provides a liquid hydrogen powered aircraft, which has four functions, namely, filling, conveying, pressure stabilization and venting, and a liquid hydrogen pump 101 is arranged in a liquid hydrogen storage tank 100 .

[0061] a) Add:

[0062] 1) Liquid hydrogen is filled into the liquid hydrogen storage tank 100 through the filling pipeline on the liquid hydrogen storage tank 100.

[0063] 2) Due to the extremely fast diffusion speed of hydrogen fuel and the need to ensure the purity of liquid hydrogen, the air in the liquid hydrogen storage tank 100 and the pipeline needs to be replaced. At the same time, due to the extremely low storage temperature of liquid hydrogen, a step-by-step refrigeration storage device is required.

[0064] 3) Therefore, when filling, it is necessary to blow and replace the liquid hydrogen storage tank 100 and the pipeline with nitrogen. First, close the safety valve 301 and the vent valve 302 on the liquid hydrogen storage tank, and perform hydrogen replacement operations on the liquid hydrogen storage tank 100, the delivery pipeline, the pressure-stabilizing pipeline and the engine 800. After the air replacement in the delivery pipeline and the pressure-stabilizing pipeline 200 is completed, close the valves of these two pipelines, and open the vent valve on the vent pipeline 300.

[0065] 4) When filling liquid hydrogen, first fill with a small flow rate to pre-cool the liquid hydrogen storage tank 100 and the pipeline, and open the vent valve 302. The other valves are closed. After all are cooled down, the flow rate can be increased.

[0066] b) Conveying function:

[0067] 1) The storage temperature of liquid hydrogen fuel is -253°C and it is stored in the liquid hydrogen storage tank 100. The liquid hydrogen fuel is pressurized by the liquid hydrogen pump 101 and then flows to the delivery pipeline.

[0068] 2) A regulating valve 102 is arranged on the delivery pipeline to control the on-off of the liquid hydrogen pipeline. When liquid hydrogen fuel is needed, this valve is opened.

[0069] 3) Liquid hydrogen needs to pass through a liquid hydrogen vaporization device 600 to vaporize the ultra-low temperature liquid hydrogen and turn it into usable hydrogen at room temperature.

[0070] 4) Since hydrogen is the smallest molecule, the flow rate and pressure are difficult to be accurately controlled by the liquid hydrogen pump 101. Therefore, a hydrogen fuel controller 400 is arranged on the delivery pipeline after the liquid hydrogen vaporization device 600. The flow regulating valve 402 on the hydrogen fuel controller 400 can accurately control the hydrogen flow rate.

[0071] 5) After the hydrogen fuel passes through the filter 401 and the flow regulating valve 402 of the hydrogen fuel controller 400, it is accurately delivered to the engine 800 after passing through the one-way valve 700, thereby providing appropriate thrust.

[0072] 6) After passing through the hydrogen fuel controller 400, the hydrogen fuel is supplied to the turbine through the one-way valve 700 and burns to generate thrust and heat.

[0073] 7) The liquid hydrogen vaporization device 600 on the delivery pipeline extracts heat from the compressor or tail nozzle 802 of the engine 800 for heat exchange with the liquid hydrogen fuel.

[0074] 8) Pressure and temperature sensors 500 are arranged behind the liquid hydrogen vaporization device 600 and the hydrogen fuel controller 400 to monitor the hydrogen parameters behind the liquid hydrogen vaporization device 600, and adjust the power of the liquid hydrogen pump 101 according to actual conditions to meet the hydrogen fuel flow demand.

[0075] c) Voltage stabilization function:

[0076] 1) As the fuel in the liquid hydrogen tank 100 is supplied to the engine 800 by the liquid hydrogen pump 101, the pressure in the liquid hydrogen tank 100 will decrease. In order to maintain the pressure in the liquid hydrogen tank 100 stable, it is necessary to ventilate the liquid hydrogen tank 100 to replenish the pressure.

[0077] 2) Since the concentration of hydrogen in the air reaches more than 4%, it is very dangerous and can be easily ignited. Therefore, air cannot be introduced into the liquid hydrogen storage tank 100 for pressure replenishment.

[0078] 3) When the pressure in the liquid hydrogen storage tank 100 drops below the normal range, the normal temperature high pressure hydrogen after passing through the liquid hydrogen vaporization device 600 is led to the liquid hydrogen storage tank 100 through the voltage regulator tube 200 to replenish the pressure.

[0079] 4) When the pressure in the liquid hydrogen storage tank 100 exceeds the normal working range, the safety valve 301 is a pressure switch to keep the pressure of the liquid hydrogen storage tank 100 stable.

[0080] d) Venting function:

[0081] 1) The venting function of this embodiment refers to the venting of the liquid hydrogen storage tank 100. This function is controlled by two valves, namely, the safety valve 301 and the venting valve 302, arranged on the liquid hydrogen storage tank 100, and a flame arrester 303 is arranged on the venting pipeline, which then leads to the atmosphere 304.

[0082] 2) This function has two main uses. One is to discharge the gas in the liquid hydrogen storage tank 100 when filling liquid hydrogen. The other is that when the system allows, when the pressure in the liquid hydrogen storage tank 100 is too high, the safety valve 301 opens to maintain the pressure of the liquid hydrogen storage tank 100.

[0083] If the liquid hydrogen pump 101 is arranged outside the liquid hydrogen storage tank 100, a small storage tank needs to be arranged separately to install the liquid hydrogen pump 101, which will increase the weight of the system. Although the liquid hydrogen pump 101 is arranged inside the liquid hydrogen storage tank 100, some fuel will be unusable due to the requirement of liquid immersion at the inlet of the liquid hydrogen pump. However, the density of liquid hydrogen is low, which saves weight compared to adding a separate liquid hydrogen pump 101 and arranging a storage tank.

[0084] The liquid hydrogen storage tank 100 and the sensor 500 arranged on the transmission pipeline are used to control the regulating valve 201 or the vent valve 302 on the voltage-stabilizing tube 200 to stabilize the pressure in the liquid hydrogen storage tank 100. The normal temperature after the liquid hydrogen vaporization device 600 is drawn from the voltage-stabilizing pipeline is higher than that of the hydrogen. When the liquid hydrogen storage tank 100 is under-pressure, a small amount of normal-temperature hydrogen is introduced. On the one hand, it increases the hydrogen in the liquid hydrogen storage tank 100. On the other hand, the heat brought by the normal-temperature hydrogen will cause part of the liquid hydrogen fuel to vaporize and replenish the pressure. If ultra-low-temperature hydrogen is used for pressure replenishment, the demand is large and it will also lead to the increase of additional equipment. This solution directly draws hydrogen from the liquid hydrogen vaporization device 600, requires less external equipment, is lighter in weight, and provides system reliability.

[0085] Liquid hydrogen fuel is vaporized in the liquid hydrogen vaporization device 600. The heat source required for heat exchange can be compressor bleed air, or heat can be extracted from the engine tail nozzle 802. After simulation calculation, the heat extracted from the tail nozzle 802 of the engine 800 can meet the heat exchange power requirement.

[0086] The liquid hydrogen storage tank 100 is provided with a liquid hydrogen filling port 900, a safety valve 301, a vent valve 302, a liquid hydrogen outlet, etc. Through these valve and pipeline combinations, liquid hydrogen filling and pressure stabilization of the liquid hydrogen storage tank 100 are achieved. Before liquid hydrogen filling, nitrogen replacement and liquid nitrogen precooling are required in the liquid hydrogen storage tank 100. When liquid hydrogen is filled, the vent valve 302 is opened to discharge nitrogen from the liquid hydrogen storage tank 100.

[0087] The pipelines after the safety valve 301 and the vent valve 302 are combined into a vent pipeline, a flame arrester 303 is arranged, and then the pipeline is introduced into the atmosphere 304. This prevents the flashback of hydrogen after combustion due to static electricity, which increases the risk of the system.

[0088] The transmission pipeline is provided with a regulating valve 102, a pressure and temperature sensor 500, a flow regulating valve 402, a one-way valve 700, etc. The hydrogen fuel on-off or hydrogen fuel flow rate is regulated by controlling the opening or opening of the valve. The one-way valve 700 is arranged after the hydrogen fuel controller 400 to prevent the hydrogen fuel from returning on the one hand, and to prevent the atmosphere from entering the front-end hydrogen system after the system is shut down on the other hand.

[0089] When demonstrating the 500kg-class twin-engine fixed-wing verification aircraft solution, it was also analyzed that the liquid hydrogen pump 101 is arranged separately outside the liquid hydrogen storage tank 100, and a separate arrangement tank for the liquid hydrogen pump 101 is required. According to the current technology, the arrangement tank for the liquid hydrogen pump and its accessories weigh about 38kg. In this embodiment, the liquid hydrogen pump is arranged in the liquid hydrogen storage tank, and this equipment is not required.

[0090] In order to replenish the pressure of the liquid hydrogen storage tank 100, it has been demonstrated that a dedicated pressure stabilizing heating device and a liquid hydrogen vaporization device are separately arranged. The pressure stabilizing heating device and the liquid hydrogen vaporization device weigh 12.1kg, the pipeline weighs 3kg, and a matching power supply is required. In this embodiment, the normal temperature and high pressure hydrogen on the transmission pipeline after passing through the liquid hydrogen vaporization device 600 is introduced into the liquid hydrogen storage tank for pressure replenishment, and the pipeline weighs 5kg. This solution reduces weight by 10.1kg.

[0091] Taking a 500kg-class verification machine as an example, after weight decomposition, the liquid hydrogen power system achieves a weight of 207.7kg after adopting the solution of the present invention; in the comparative example, the liquid hydrogen pump 101 is arranged outside the liquid hydrogen storage tank 100 and the voltage stabilization system is arranged separately, and the liquid hydrogen power system solution requires 255.8kg. The solution of the present invention reduces the weight by 48.1kg in total, a weight reduction of 18.8%.

[0092] The contents not described in detail in this specification belong to the prior art known to professional and technical personnel in this field.

[0093] The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiment. Any equivalent modifications or changes made by those skilled in the art based on the contents disclosed by the present invention should be included in the protection scope recorded in the claims.

Claims

1. A liquid hydrogen powered aircraft, characterized in that: include: A liquid hydrogen storage system comprises a liquid hydrogen storage tank (100) for storing liquid hydrogen, a liquid hydrogen pump (101) being arranged in the liquid hydrogen storage tank (100), and the liquid hydrogen pump (101) being used to transport the liquid hydrogen to a liquid hydrogen vaporization device (600); A liquid hydrogen vaporization device (600) for converting liquid hydrogen into normal temperature and high pressure hydrogen; Fuel delivery and control system, used to deliver room temperature and high pressure hydrogen to the combustion system; The combustion system comprises an engine (800) having a combustion chamber (801), wherein hydrogen is burned in the combustion chamber (801) to generate thrust; heat generated during combustion is obtained through a bleed air or tail nozzle (802) as a heat source for a liquid hydrogen vaporization device (600); under the action of the heat source, liquid hydrogen is vaporized after passing through the liquid hydrogen vaporization device (600) and reaches a combustible state.

2. A liquid hydrogen powered aircraft according to claim 1, characterized in that: A liquid hydrogen filling port is provided on the top of the liquid hydrogen storage tank (100), and a filling pipeline (900) is connected to the liquid hydrogen filling port for filling liquid hydrogen into the liquid hydrogen storage tank (100); The filling pipeline (900) is provided with a regulating valve.

3. A liquid hydrogen powered aircraft according to claim 1, characterized in that: The liquid hydrogen storage tank (100) is provided with a venting pipeline (300) for safely discharging liquid hydrogen when necessary to prevent accidents; The liquid hydrogen storage tank (100) is connected to the venting pipeline (300) via a first connecting pipeline, and a safety valve (301) is provided on the first connecting pipeline; The venting pipeline (300) is connected to the atmosphere (304) after passing through the flame arrester (303).

4. A liquid hydrogen powered aircraft as claimed in claim 3, characterized in that: A pressure-stabilizing pipeline (200) is provided between the liquid hydrogen vaporizing device (600) and the liquid hydrogen storage tank (100) for controlling the pressure of the liquid hydrogen storage tank (100); The pressure stabilizing pipeline (200) is connected to the second regulating valve (201), the second regulating valve (201) is directly connected to the liquid hydrogen storage tank (100) via the second connecting pipeline, the second regulating valve (201) is also connected to the vent valve (302) via the third connecting pipeline, and the vent valve (302) is connected to the vent pipeline (300) between the safety valve (301) and the flame arrester (303).

5. A liquid hydrogen powered aircraft as claimed in claim 1, characterized in that: The liquid hydrogen pump (101) is connected to the liquid hydrogen vaporization device (600) via a fourth connecting pipeline; The fourth connecting pipeline is provided with a first regulating valve (102).

6. A liquid hydrogen powered aircraft as claimed in claim 1, characterized in that: A fuel delivery pipeline is provided between the liquid hydrogen vaporization device (600) and the engine (800); A first pressure and temperature sensor (501), a hydrogen fuel controller (400), a second pressure and temperature sensor (502) and a one-way valve (700) are sequentially arranged on the fuel delivery pipeline; The hydrogen fuel controller (400) comprises a filter (401) and a flow regulating valve (402) and is used to accurately control the flow and pressure of hydrogen.

7. A liquid hydrogen powered aircraft as claimed in claim 1, characterized in that: The liquid hydrogen storage tank (100) is provided with a pressure and temperature monitoring system for safety monitoring; The pressure and temperature monitoring system comprises: a liquid level sensor L, a temperature sensor T and a pressure sensor P arranged in the liquid hydrogen storage tank (100), and is used to monitor the state in the liquid hydrogen storage tank (100).

8. A liquid hydrogen powered aircraft as claimed in claim 1, characterized in that: When the pressure in the liquid hydrogen storage tank (100) exceeds the normal working range, the safety valve (301) automatically opens as a pressure switch, and automatically closes when the pressure in the liquid hydrogen storage tank (100) returns to the normal working range, thereby maintaining the pressure of the liquid hydrogen storage tank (100) stable.

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