2079 results about "Liquid hydrogen" patented technology

An aircraft thermal management system comprising a high temperature loop and a low temperature loop. The high temperature loop is configured to manage a temperature of a fuel cell stack in a nacelle using a nacelle heat exchanger. The low temperature loop is configured to cool a number of heat loads in a nacelle using a heat capacity of liquid hydrogen.

The invention provides a fuel cell hydrogen supply system and a hydrogen supply method. The fuel cell hydrogen supply system comprises a liquid hydrogen storage tank, a first gas path connected between the liquid hydrogen storage tank and a fuel cell, a second gas path connected in parallel with the first gas path, and a control assembly, a gasification device is arranged on the first gas path, and a gas storage bottle is arranged on the second gas path; the control assembly comprises a controller and a plurality of control valves; the controller controls the plurality of control valves and can respectively control the connection or disconnection of the first gas path and the second gas path, so that the liquid hydrogen in the liquid hydrogen storage tank is conveyed to the fuel cell through the first gas path, and when the pressure of the gaseous hydrogen in the liquid hydrogen storage tank exceeds a first preset pressure threshold value, the gaseous hydrogen is stored in the gas storage bottle through the second gas path; and hydrogen can be supplied to the fuel cell through the second gas path. According to the fuel cell hydrogen supply system, gaseous hydrogen exceeding the first preset pressure threshold in the liquid hydrogen storage tank can be recycled, so that the release of the gaseous hydrogen to the outside is reduced, and the waste of resources is reduced.

Methods and systems providing a process for cooling and liquefying a purified gaseous hydrogen feed stream to a liquid hydrogen stream that may be stored in a liquid hydrogen storage tank, as well as a system wherein ortho-hydrogen (o-H2) contained in the purified gaseous hydrogen feed stream may be converted to para-hydrogen (p-H2) through serial low-temperature catalytic converters along the cooling process from normal ambient temperature (300K) to the liquefied temperature about (20K) of the hydrogen.

The invention discloses a liquid hydrogen storage tank pressure prediction method, device and system, and the method comprises the steps: obtaining process parameters of a liquid hydrogen storage tank, and carrying out the preprocessing, and obtaining input parameters; and inputting the input parameters into the trained liquid hydrogen storage tank pressure prediction model, and outputting an in-tank pressure prediction value of the liquid hydrogen storage tank after the predicted storage duration. According to the method, the adverse effect on the generalization performance of the neural network due to too few data samples is reduced, and the precision of predicting the pressure of the liquid hydrogen storage tank is effectively improved.

An aircraft comprises a fuselage; wings; engines connected to the wings; a set of liquid hydrogen tanks; a vent located on the tail on the fuselage; a conduit system connecting the liquid hydrogen tanks to the vent; and a controller. The controller is configured to control the conduit system to remove gaseous hydrogen in the set of liquid hydrogen tanks to travel through the conduit system and exit at the vent in response to pressure in the set of liquid hydrogen tanks being greater than a specified tolerance.

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.

The invention relates to a cathode closed type air-cooled fuel cell for an unmanned aerial vehicle and a working method of the cathode closed type air-cooled fuel cell. The fuel cell comprises a hydrogen supply subsystem, an oxygen supply subsystem, a cooling path subsystem and an electric pile, the hydrogen supply subsystem and the oxygen supply subsystem complete heat exchange between liquid hydrogen and high-temperature air through a liquid hydrogen vaporizer, and the effects of liquid hydrogen vaporization and high-temperature air cooling are achieved. By arranging the first vortex tube to replace a traditional pressure reducing valve, potential energy of vaporized high-pressure hydrogen is recovered by the first vortex tube, the vaporized high-pressure hydrogen is separated into cold flow and hot flow in the first vortex tube, and the hot flow partially enters an end plate of the galvanic pile to heat the end plate, so that the temperature distribution in the galvanic pile is optimized, and the voltage consistency between single cells is improved; therefore, the performance and durability of the stack are improved. When the fuel cell is used for the unmanned aerial vehicle, the fan of the fuel cell is also used as a propeller of the unmanned aerial vehicle, so that the system integration level is increased.

The present disclosure provides active venting control systems for use with liquid hydrogen tanks. The active venting control system allows a greater mass of hydrogen to be safely stored for a greater period of time. The systems is configured to actively monitor, control, and vent hydrogen based on a combination of pressure and fill level within the tank. When the tank reaches a predetermined fill level, the active venting control system is configured to vent the tank for a predetermined period of time. The active venting control system is configured to repeat the process during a transit and storage time, allowing the tank to be filled with a higher initial fill level and hold a greater mass of hydrogen compared to passive pressure relief systems.

A fuel system for a hydrogen fueled gas turbine engine comprises a main hydrogen fuel storage unit configured to store liquid hydrogen. The main fuel storage unit comprises an ullage space configured to store ullage fluid comprising gaseous or supercritical hydrogen. The system further comprises a liquid hydrogen drain line configured to provide liquid hydrogen from the main hydrogen fuel storage unit to a fuel conduit, the fuel conduit being configured to supply hydrogen fuel to a combustor of the gas turbine engine. A priming line is provided, which is configured to provide ullage fluid to the fuel conduit, and a priming valve is configured to selectively control flow through the priming line.

The invention discloses a hydrogen supply and energy storage device which comprises a hydrogen storage tank body, a gaseous hydrogen storage tank is installed in the hydrogen storage tank body, a liquid hydrogen storage tank is installed on the hydrogen storage tank body, a supporting plate is fixedly connected to the hydrogen storage tank body, and a cooling liquid storage box is installed at the top end of the supporting plate. A transverse plate is fixedly connected to the side wall of the cooling liquid storage box, metal cooling fins are arranged on the side wall of the transverse plate, and the cooling device further comprises a cooling circulation assembly and an air blowing cleaning assembly. A motor drives a first sector gear to rotate, the first sector gear is alternately engaged with a transmission gear and a driven gear, so that a rotating shaft drives metal heat dissipation fins to rotate for heat dissipation, and meanwhile, the driven gear drives cooling liquid to circularly flow in a sealing pipe, a cooling pipe and a liquid inlet pipe through a connecting rod and a piston rod; and cold airflow generated by the fan is used for dissipating heat of the hydrogen conveying pipe, so that the heat dissipation effect is improved.

The utility model provides a vehicle-mounted liquid hydrogen storage tank and a vehicle, and relates to the field of vehicle engineering technology. The vehicle-mounted liquid hydrogen storage tank comprises: a tank body and a spiral rib installed inside the tank body, and the outer ring of the spiral rib is welded to the tank body. Compared with welding multiple baffles separately, the processing efficiency is higher, which is conducive to reducing the production cost of the liquid hydrogen storage tank. The spiral rib can separate the impact of liquid hydrogen, and can also separate the thermal stratification caused by heat leakage, shaking and flashing. The temperature difference of each divided part is small, and then the overall temperature difference is also small, which reduces the degree of thermal stratification to a certain extent, thereby achieving the technical effects of preventing liquid hydrogen from shaking and reducing the degree of thermal stratification.

In order to improve liquid hydrogen storage on aircraft, a liquid hydrogen tank is integrated into the fuselage of the aircraft. At least one portion of the tank wall is formed by specially adapted tank skin panels and / or a pressure bulkhead. The parts forming the tank wall are strengthened to contain a tank pressure of about 3 bar.

The gradually-expanded printed circuit board type heat exchange inner core comprises a cover plate, a bottom plate, a cold side plate layer and a hot side plate layer, a cold side gradually-expanded channel is of a flow channel structure with the width gradually expanded, and the sectional area of a flow channel dynamically adapts to gas-liquid phase change and volume change. And pressure drop fluctuation and bubble aggregation caused by gas phase expansion are reduced, the shunt channels and the divergent channels are arranged in parallel, an inner wall porous structure is combined, medium distribution uniformity is optimized through graded distribution and surface wettability enhancement, and the flow stability is remarkably improved. The turbulent flow ribs are arranged in the heat exchange channel on the heat side, combination of heterogeneous working media such as supercritical CO2-water and liquid hydrogen-liquid oxygen is supported by destroying a heat boundary layer, inducing turbulent flow and strengthening convective heat exchange and phase change heat transfer, the heat exchanger can improve the heat exchange efficiency while reducing pressure drop, compactness, reliability and wide working condition adaptability are considered, and the heat exchange efficiency is improved. Two-phase flow optimization and efficient heat exchange are achieved, and the extreme heat exchange requirements in the fields of aerospace, new energy and the like are met.

The invention belongs to the technical field of aviation electric propulsion, and relates to a hydrogen fuel cell superconducting hybrid electric propulsion system based on hydrogen and helium heat exchange cooling, which is suitable for megawatt level branch aircrafts and comprises a liquid hydrogen storage tank, a hydrogen and helium heat exchanger, a hydrogen fuel cell, a lithium battery, an inverter, a superconducting motor, a propeller and other core components. The liquid hydrogen storage tank vaporizes liquid hydrogen through the micro-channel plate type hydrogen-helium heat exchanger and stably supplies the vaporized liquid hydrogen to the hydrogen fuel cell to generate electric energy; helium is used for a low-temperature cooling loop and cooling key assemblies such as a superconducting motor, a low-temperature inverter, a superconducting cable and a hydrogen fuel cell, and it is ensured that the key assemblies stably operate at the optimal working temperature. The hydrogen fuel cell and the lithium battery cooperatively provide electric energy for the superconducting electric propulsion system, the integrated energy management controller dynamically adjusts the output power of the fuel cell and the lithium battery by adopting a state machine strategy, and accurate monitoring and optimal distribution of working parameters of all components are achieved. The optimal heat balance and power output are ensured to be realized in different flight stages such as takeoff, cruise and landing; according to the hydrogen fuel cell hybrid electric propulsion system based on hydrogen and helium heat exchange cooling, the power generation efficiency and the operation stability of the hydrogen fuel cell are remarkably improved, the overall energy conversion efficiency is improved, and the high-power and high-efficiency power extraction requirements of megawatt aircrafts are fully met.

The invention discloses a liquid hydrogen fuel energy power system and an airplane, and belongs to the technical field of liquid hydrogen airplane power device system integration. The system comprises a liquid hydrogen tank, a liquid hydrogen pipeline, a gas hydrogen pipeline, a heat conduction liquid circulation pipeline, an air pipeline, a hydrogen turbine engine power device, a fuel cell, a heating device, a primary heat exchanger, a secondary heat exchanger, a starter and an airborne power supply and distribution network. The system absorbs waste heat of a fuel cell and exhaust waste heat of an engine exhaust nozzle, liquid-gas-hydrogen conversion is achieved, and the problem of vaporization of liquid hydrogen fuel on a machine is effectively solved. Pressurized air is provided for the fuel cell through air entraining of an engine air compressor, waste heat of the fuel cell is absorbed through a first-stage heat exchanger, and the air side supply and heat dissipation functions of the fuel cell are achieved. According to the two-stage heat exchange device, fuel vaporization heating with different hydrogen fuel flow supply requirements is achieved according to the starting and stable operation processes, the system starting method solves the system starting heat source problem, and combined starting of the main power device and the auxiliary power device is achieved.

The utility model relates to a liquid hydrogen storage tank with a vaporizer. Comprising an inner shell used for containing liquid hydrogen; the pressurizing unit comprises a pressurizing pipeline, and a pressurizing valve, a pressurizer and a pressurizing and pressure regulating valve which are sequentially arranged on the pressurizing pipeline in the medium flowing direction; one end of the pressurizing pipeline is connected with the bottom end of the inner shell, and the other end is communicated with the gas-phase space of the inner shell; the pressurizing unit is used for maintaining the pressure of the inner shell at a first pressure; the air supply unit comprises an air supply pipeline, and an air supply valve, a vaporizer, a pressure reducing valve and a check valve which are sequentially arranged on the air supply pipeline in the medium flowing direction; one end of the gas supply pipeline is connected with the bottom end of the inner shell, and the other end is connected with external gas utilization equipment; the vaporizer is used for converting liquid hydrogen into hydrogen, and the pressure reducing valve is used for reducing the pressure of the gasified hydrogen to the pressure required by gas equipment; and the exhaust unit is communicated with the gas phase space of the inner shell and is used for exhausting the overpressure gas. According to the storage tank, gas supply parameters can be changed according to gas use requirements of users, and the applicability is high.

A hydrogen aircraft includes: an airframe including a fuselage and a wing; at least one propulsion system fixed to the airframe; a pressurized chamber disposed inside the fuselage; a pressure bulkhead that is disposed at a rear part of the pressurized chamber and has strength to withstand pressurization of the pressurized chamber; a hydrogen tank that is disposed in an accommodation section and stores liquid hydrogen, the accommodation section being installed behind the pressure bulkhead, outside the pressurized chamber, and inside the fuselage; and a supply line that supplies the liquid hydrogen stored in the hydrogen tank to the propulsion system.

The invention relates to a hydrogen supply system and a new energy automobile. The system comprises a liquid hydrogen module and a gas hydrogen module, wherein the liquid hydrogen module and the gas hydrogen module are used for respectively providing hydrogen and high-pressure hydrogen subjected to first pressurization treatment for a pressurization module; the first side of the recovery module is connected with the liquid hydrogen module, and the recovery module is used for receiving recovered gas hydrogen discharged by the liquid hydrogen module and obtaining pressurized recovered gas hydrogen; the second side of the recovery module is connected with the gas hydrogen module and is used for transmitting the pressurized recovered gas hydrogen to the gas hydrogen module; the pressurizing module is used for performing second pressurizing treatment and third pressurizing treatment on the hydrogen subjected to the first pressurizing treatment and the high-pressure hydrogen to obtain pressurized target hydrogen; the buffer module is used for supplying the supercharged target hydrogen to the engine module. By adopting the hydrogen supply system, under the condition of low liquid hydrogen storage pressure, the liquid hydrogen supply pressure can be effectively maintained, stable operation of a fuel cell is guaranteed, meanwhile, evaporated hydrogen of the liquid hydrogen system is recycled, the energy utilization rate is increased, and then the power and cruising ability of a vehicle are guaranteed.

To suppress hydrogen concentration in surrounding atmosphere to a determined reference value or less by detecting a change in the hydrogen concentration if liquefied hydrogen leaks.SOLUTION: A liquefied hydrogen pump system includes a liquefied hydrogen pump and a control device, and the liquefied hydrogen pump includes a cylinder, a piston, a rod, a drive part, and a seal part. The seal part includes a first seal member, a second seal member provided with an interval in the direction of separating from the piston an axial direction with respect to the first seal member, a flow passage part, one end of which communicates with a gap between the rod and the cylinder and the other end of which opens to the outside of the cylinder, and an information acquisition part for acquiring information on hydrogen concentration in a fluid flowing to the outside of the cylinder through the flow passage part. The control device stops the operation of the liquefied hydrogen pump in the case of determining that hydrogen concentration in the fluid exceeds a preset reference value on the basis of information on the acquired hydrogen concentration.SELECTED DRAWING: Figure 2

The invention relates to the technical field of liquid hydrogen storage and transportation, and discloses a liquid hydrogen container heat insulation performance rapid detection method, which comprises: S1, measuring the specification of a liquid hydrogen container and the initial state parameter in the liquid hydrogen container; s2, calculating initial parameters of liquid hydrogen and hydrogen in the liquid hydrogen container; s3, the change rate of the state parameters in the liquid hydrogen container is measured, and the final state parameters in the liquid hydrogen container are monitored; s4, calculating final parameters of liquid hydrogen and hydrogen in the liquid hydrogen container; s5, calculating the evaporation mass flow rate of the gas-liquid interface of the liquid hydrogen container according to the change rate of the state parameters in the liquid hydrogen container; s6, the thermodynamic energy change rate of hydrogen and liquid hydrogen in the liquid hydrogen container is calculated; s7, calculating the total internal energy change of the liquid hydrogen container, and calculating the total heat transfer amount of the gas phase and the liquid phase of the liquid hydrogen container; and S8, comparing the total heat transfer amount of the gas phase and the liquid phase of the liquid hydrogen container with standard static evaporation rate data to obtain the heat insulation performance of the liquid hydrogen container. The detection method has the characteristics that hydrogen does not need to be discharged, and the detection precision and safety are improved.

The invention discloses a liquid hydrogen container heat leakage prediction and boost characteristic detection method and system. The method comprises the following steps: establishing a three-dimensional heat flow field model of a liquid hydrogen container; calculating the heat flow density of a gas-liquid interface based on the three-dimensional heat flow field model so as to adjust the liquid hydrogen evaporation capacity; total heat leakage is obtained through finite element simulation and experimental data collaborative calibration; calculating a static evaporation rate according to the total heat leakage; establishing a nonlinear mapping model of the static evaporation rate and the boost rate through a response surface regression method; the wall temperature distribution of the liquid hydrogen container is monitored in real time, thermophysical parameters are calibrated through the LSTM neural network by adopting a dynamic calibration algorithm, and the output result of the three-dimensional heat flow field model is corrected. By establishing a three-dimensional heat flow field model of the liquid hydrogen container, determining a nonlinear response relationship between the evaporation rate and the pressure rising rate of the liquid hydrogen container, and constructing a cloud-edge collaborative detection system, the heat leakage performance of the liquid hydrogen container is accurately predicted, and efficient pressure rising rate detection is realized.

The liquid hydrogen evaporation rate detection method of the liquid hydrogen container comprises the following steps that the evaporation rate of liquid hydrogen in the liquid hydrogen container is obtained through a flow detection method, and the evaporation rate is a first evaporation rate A; the evaporation rate of liquid hydrogen in the liquid hydrogen container is obtained through a weighing detection method and serves as a second evaporation rate B; carrying out weight calculation on the first evaporation rate A and the second evaporation rate B to obtain a liquid hydrogen evaporation rate detection value alpha of the liquid hydrogen container; converting flow data detected by the flow detection method into a weight coefficient as a first weight coefficient M of the first evaporation rate A; converting weighing data detected by the weighing detection method into a weight coefficient as a second weight coefficient M of the second evaporation rate B; the liquid hydrogen evaporation rate alpha is obtained according to the sum of the product of the first evaporation rate A and the first weight coefficient M and the product of the second evaporation rate B and the second weight coefficient N; a standard flow detection method and a weighing detection method are combined to comprehensively obtain a liquid hydrogen evaporation rate detection value of the liquid hydrogen container, and the detection value can reflect the actual evaporation rate of the liquid hydrogen container.

According to the liquid hydrogen refueling station cold energy recovery system and the control method, the cold energy recovery system comprises a liquid hydrogen pump and a gas hydrogen buffer tank, a cold energy recovery device is arranged between the liquid hydrogen pump and the gas hydrogen buffer tank, and the cold energy recovery device comprises at least one stage of thermoacoustic engine and at least one stage of pulse tube refrigerator; the thermoacoustic engine can recover cold energy released when liquid hydrogen flows through the thermoacoustic engine and drive the pulse tube refrigerator to conduct refrigeration. According to the cold energy recovery system, the low-temperature fluid flows through the cold energy recovery device to absorb heat and then enters the gas hydrogen buffer tank to be stored, the thermo-acoustic engine in the cold energy recovery device is driven by the cold capacity of the low-temperature fluid, meanwhile, the thermo-acoustic engine converts the cold capacity into acoustic power and then transmits the acoustic power to the pulse tube refrigerator for refrigeration, the conversion efficiency is high, and the energy consumption is low. Efficient recovery of cold energy is achieved, and cold energy lost in the temperature rising process of low-temperature fluid can be effectively recovered.

An aircraft includes a fuselage, a wing connected to the fuselage, an engine connected to the wing, and a liquid hydrogen tank. Each of the engines includes a nacelle, an electric motor within the nacelle, a fuel cell stack within the nacelle, and a nacelle heat exchanger within the nacelle that receives air flowing through a nacelle inlet. The liquid hydrogen tank is configured to store liquid hydrogen, wherein the liquid hydrogen tank extends along an exterior of the fuselage and above the wings and below a window in the fuselage.

The invention discloses a fuel cell stack air inlet system and a vehicle. The system comprises an air compressor, a vaporization device, a liquid hydrogen bottle and a fuel cell stack, wherein a first inlet of the vaporization device is connected with the liquid hydrogen bottle, and a first outlet of the vaporization device is connected with an anode inlet of the fuel cell stack; an air outlet of the air compressor is connected with a second inlet of the vaporization device, and the air compressor is configured to heat the liquid hydrogen in the vaporization device before the fuel cell stack works so as to vaporize the liquid hydrogen. According to the fuel cell stack gas inlet system, high-temperature gas generated by the air compressor can be used for providing a heat source for liquid hydrogen vaporization, and the heat source problem of liquid hydrogen vaporization before the fuel cell stack is started is solved.

The invention discloses 15Ni steel for an ultralow-temperature liquid hydrogen storage tank and a preparation method of the 15Ni steel, and belongs to the technical field of metallurgy. The 15Ni steel comprises the following chemical components in percentage by mass: 0.02%-0.07% of C, 0.10%-0.30% of Si, 0.20%-0.80% of Mn, 0.15%-0.30% of Mo, 0.020%-0.050% of Al, 12.5%-15.5% of Ni, 0.0015%-0.0060% of N, less than or equal to 0.008% of P, less than or equal to 0.002% of S, less than or equal to 0.020% of Nb, less than or equal to 0.080% of V, less than or equal to 0.020% of Ti and the balance of Fe and inevitable impurities. The preparation method comprises the procedures of smelting, continuous casting, heating, rolling and heat treatment. The steel plate produced by the invention has excellent ultralow temperature (-269 DEG C) impact toughness, effectively solves the problems of brittle phase martensite precipitation and low strength of stainless steel at a low temperature of-196 DEG C, can replace stainless steel to be widely used for manufacturing large ultralow temperature liquid hydrogen storage tanks, and has wide application prospects.

The invention discloses a method for obtaining hydrogen solubility in slag based on microstructure analysis, and belongs to the field of high-temperature melt physical property characterization. The method comprises the following steps: determining initial components of a simulation system; establishing an initial structure model of the water molecule-containing slag system; determining a potential function for describing the simulation system; simulation calculation parameters are set, LAMMPS software is operated for simulation calculation, and simulation result data such as an atomic coordinate file and free energy of a simulation system are obtained; the atomic coordinate file is imported into visual software for statistical analysis and visual processing, and microstructure information of the slag is obtained; and calculating the hydrogen solubility of the slag according to simulation result data such as free energy. According to the method, the microstructure information of the atomic scale of the slag and the hydrogen solubility of the slag are calculated by adopting a molecular dynamics simulation method, so that the blank of experimental data can be filled, theoretical guidance is provided for controlling the hydrogen content of the slag, and a theoretical foundation is laid for controlling the hydrogen content of the molten steel.

A hydrogen storage and delivery system delivering storing and dispensing cryogenic liquid and gaseous hydrogen, comprising cryogenic liquid hydrogen storage vessels with heaters 1, 2, 3, ambient tempe

The invention relates to a liquid hydrogen storage tank liquid level meter based on an ultrasonic ranging technology, which comprises a floater, a floater limiting net cylinder, an ultrasonic ranging probe, an aviation plug, a cable and a computer, and ensures the effectiveness and reliability of the liquid level meter under the design condition of a liquid hydrogen tank. The buoy liquid level meter and the ultrasonic ranging technology are combined, and compared with a traditional capacitive liquid level meter, the liquid level meter has the advantages of being small in size, convenient to install and low in cost.

The invention provides a multiphase hydrogen fuel flow and pressure cooperative control system, and belongs to the technical field of aero-engines, the multiphase hydrogen fuel flow and pressure cooperative control system comprises a liquid hydrogen tank, a liquid hydrogen pump, a heat exchanger, a pressure stabilizing valve, a regulating valve, a stop valve, a sensor and an engine main controller, the engine main controller receives engine state feedback and outputs a hydrogen fuel mass flow instruction; the pressure maintaining valve outlet pressure instruction calculation module and the pressure maintaining valve pressure closed-loop control module are arranged between the pressure maintaining valve and the engine, and the liquid hydrogen pump outlet pressure instruction calculation module and the liquid hydrogen pump outlet pressure compensation control module are arranged between the liquid hydrogen pump and the engine. The regulating valve outlet flow lead correction control module is arranged between the regulating valve and the engine; according to the scheme, the rotating speed of the liquid hydrogen pump, the opening area of the pressure maintaining valve and the opening area of the adjusting valve are cooperatively controlled, flow and pressure dynamic matching of the hydrogen fuel adjusting system under the non-stable working condition is achieved, and the flow control dynamic response performance of the hydrogen fuel adjusting system is improved.