Novel liquid hydrogen storage tank device with multi-layer cold insulation structure and working method of novel liquid hydrogen storage tank device

Abstract

The invention discloses a novel liquid hydrogen storage tank device with a multi-layer cold insulation structure and a working method of the novel liquid hydrogen storage tank device, a cryogenic phase change material layer is additionally arranged in a liquid hydrogen storage tank, and the problem of high daily evaporation rate of a traditional liquid hydrogen storage tank is solved by utilizing the characteristic that a phase change material stores cold energy; a partition plate is arranged in the liquid hydrogen storage tank, so that the problem that the liquid hydrogen in the storage tank shakes greatly due to take-off and landing of an airplane is solved; the supporting structure is completely made of glass fiber reinforced plastic materials, a cavity is designed inside, and the defect that a traditional supporting structure is prone to heat leakage is overcome. A liquid hydrogen pump is arranged in a liquid phase in the storage tank, liquid hydrogen rises to a certain pressure to be combusted by an engine, in addition, a hydrogen pressure relief opening is connected with a hydrogen fuel cell system, power can be supplied to a pump on an airplane, remaining power can be supplied to other facilities, and generated water can be used for cooling the engine of the airplane. The problems of insufficient utilization of liquid hydrogen and single use condition are solved. The device has the advantages of being good in cold insulation effect, low in daily evaporation rate, good in stability and high in energy utilization rate.

Description

Technical Field

[0001] The invention belongs to the technical field of liquid hydrogen storage devices, and particularly relates to a novel multi-layer cold insulation structure liquid hydrogen storage tank device and a working method thereof. Background Art

[0002] With the increasing prominence of energy and environmental problems in recent years, countries around the world are actively developing clean energy technologies and issuing corresponding reports, aiming to change the energy consumption structure through scientific and technological innovation and achieve the sustainable development of global green energy. Hydrogen has the advantages of high calorific value and environmental friendliness. The calorific value of hydrogen is 140 MJ / kg, while that of gasoline is only 46 MJ / kg. Therefore, hydrogen is an ideal energy source to replace traditional hydrocarbon fuels. Moreover, the products of hydrogen combustion or electrochemical reactions are water, meeting the requirements of environmental sustainable development. In the field of aerospace transportation, liquid hydrogen also has broad application prospects. Since liquid hydrogen has better high-altitude combustion characteristics than other fuels, it can extend the in-air time of aircraft as much as possible.

[0003] However, due to the properties of liquid hydrogen such as low density, low boiling point, and strong diffusivity, it brings great difficulties to the storage of liquid hydrogen, which is also one of the key problems restricting the large-scale use of liquid hydrogen. Existing liquid hydrogen storage and transportation equipment adopts a double-layer shell structure + vacuum insulation material, with a minimum daily evaporation rate of 0.7%. Further reducing the daily evaporation rate faces challenges of high-performance insulation materials. Moreover, in order to resist huge temperature difference stresses, at least 5-10% of liquid hydrogen needs to be retained in the tank to maintain the low temperature state of the tank, resulting in poor economy of such liquid hydrogen equipment. At the same time, it faces huge transportation safety hazards.

[0004] In addition, liquid hydrogen storage tanks applied to aircraft also face great difficulties. Since aircraft will face huge overweight and weightlessness phenomena during takeoff and landing, it causes violent sloshing of liquid hydrogen in the storage tank, which will seriously affect the flight safety of the aircraft. This is an urgent problem to be solved. Through investigation, it is found that the existing airborne liquid hydrogen storage tanks also have the following deficiencies: First, in the existing liquid hydrogen storage tanks, the support structure between the storage tanks is prone to heat leakage, resulting in an increase in the evaporation rate of liquid hydrogen. Moreover, after the inner tank of the storage tank is filled with liquid hydrogen and cools down and shrinks, it will rigidly pull the support structure, easily causing the connection strength to deteriorate, thereby affecting the service life of the storage tank. Second, in the existing liquid hydrogen storage tanks, the pressure and temperature of liquid hydrogen and hydrogen in the storage tank are monitored inaccurately, resulting in the inability to discharge the evaporated hydrogen in time, easily causing safety hazards such as storage tank explosion. Third, in the existing liquid hydrogen storage tanks, when discharging pressure, the cold energy of the low-temperature evaporated hydrogen is not utilized, but directly discharged outside the storage tank, which will cause a large amount of cold energy loss. Summary of the Invention

[0005] In view of the above deficiencies of the prior art, the present invention provides a novel multi-layer cold insulation structure liquid hydrogen storage tank device and its working method, which solve the problems that the cold energy of the evaporated hydrogen in the existing liquid hydrogen storage tank is directly discharged without being utilized, the pressure and temperature of the evaporated hydrogen in the storage tank are inaccurately monitored and cannot be discharged in time, the large amplitude shaking of the storage tank during flight, and the heat leakage and poor connection strength are easily caused by the internal and external tank support structures.

[0006] To achieve the above technical objectives, the technical solutions adopted by the present invention are as follows:

[0007] A novel multi-layer cold insulation structure liquid hydrogen storage tank device, comprising a hydrogen storage tank main body, a cold insulation material module, a support structure module, a liquid hydrogen injection and output module, a vacuum pumping module, a phase change material injection and discharge module, and an automatic controller;

[0008] Among them, the interior of the hydrogen storage tank main body includes liquid hydrogen, a gas hydrogen heat exchanger, a gas hydrogen outlet, and an anti-slosh baffle is provided inside; the gas hydrogen heat exchanger is connected to the gas hydrogen outlet, and the gas hydrogen outlet is connected to a gas hydrogen power generation branch;

[0009] The cold insulation material module is divided into an intermediate section, a first dome protection layer and a second dome protection layer, all of which include a liquid hydrogen vacuum layer, a liquid hydrogen phase change material layer, and a thermal insulation layer sequentially wrapped outside the hydrogen storage tank main body. An alarm device and a fifth pressure sensor are connected to the outside of the second dome protection layer by screws;

[0010] The support structure module includes a number of support structures for supporting each layer in the cold insulation material module, and is connected to the stainless steel layer of the liquid hydrogen storage tank;

[0011] The liquid hydrogen injection and output module is arranged in the first dome protection layer, including a first solenoid valve, a liquid hydrogen inlet, a liquid hydrogen pump, and a liquid hydrogen outlet, and the output end is connected to a liquid hydrogen combustion branch;

[0012] The vacuum pumping module is arranged in the liquid hydrogen vacuum layer, including a vacuum pumping port, a second solenoid valve, and a fourth pressure sensor. The automatic controller monitors the pressure of the fourth pressure sensor and controls the opening degree of the second solenoid valve to ensure safety during vacuum pumping;

[0013] The phase change material injection and discharge module is arranged in the liquid hydrogen phase change material layer, including a phase change material inlet, a third solenoid valve, an ultrasonic flaw detector sensor, a phase change material outlet, and a fourth solenoid valve. The opening degree of the third solenoid valve is controlled by the automatic controller monitoring the liquid level of the phase change material, and the corrosion of the liquid hydrogen storage tank wall by the phase change material is monitored by the ultrasonic flaw detector sensor to ensure that the main material of the storage tank is in a safe hydrogen storage state.

[0014] To optimize the above technical solutions, the specific measures taken also include:

[0015] The above-mentioned gaseous hydrogen power generation branch includes a check valve, a first pressure sensor, a first temperature sensor, a first flow sensor, a hydrogen gas evacuation port, a sixth solenoid valve, a hydrogen fuel cell system, an oxygen cylinder, a seventh solenoid valve, and a gaseous hydrogen pump;

[0016] The first end of the gaseous hydrogen outlet is connected to the heat exchanger, and the second end is connected to the first end of the check valve through a pipeline. The second end of the check valve is sequentially connected to the first end of the first pressure sensor, the first temperature sensor, and the first flow sensor through pipelines. The second end of the first flow sensor is connected to the first end of the hydrogen gas evacuation port. The second end of the hydrogen gas evacuation port is respectively connected to the first end of the sixth solenoid valve and the first end of the seventh solenoid valve through pipelines. The second end of the sixth solenoid valve is connected to the first end of the hydrogen fuel cell through a pipeline. The second end of the seventh solenoid valve is connected to the first end of the gaseous hydrogen pump through a pipeline. The second end of the hydrogen fuel cell is connected to the oxygen tank through a pipeline, and the third end of the hydrogen fuel cell is connected to the second end of the gaseous hydrogen pump through an electric wire. The third end of the gaseous hydrogen pump is connected to the aircraft engine through a pipeline.

[0017] The above-mentioned liquid hydrogen combustion branch includes a second pressure sensor, a second temperature sensor, a second flow sensor, a fifth solenoid valve, a booster vaporizer, a third pressure sensor, a third temperature sensor, a third flow sensor, an eighth solenoid valve, and an aircraft engine, which are connected in sequence;

[0018] The first end of the liquid hydrogen outlet is connected to the first end of the second pressure sensor through a pipeline. The second end of the second pressure sensor is sequentially connected to the first end of the second temperature sensor and the second flow sensor through pipelines. The second end of the second flow sensor is connected to the first end of the fifth solenoid valve through a pipeline. The second end of the fifth solenoid valve is connected to the first end of the booster vaporizer through a pipeline. The second end of the booster vaporizer is sequentially connected to the first end of the third pressure sensor, the third temperature sensor, and the third flow sensor through pipelines. The second end of the third flow sensor is connected to the first end of the eighth solenoid valve through a pipeline. The second end of the eighth solenoid valve is connected to the aircraft engine through a pipeline;

[0019] The cooling capacity of the booster vaporizer is sent into the aircraft engine, the hydraulic system, and the electrical system by the cooling water pump to cool the three respectively, realizing the efficient utilization of the cooling capacity. The generated water is discharged outside the aircraft through the aircraft drain port.

[0020] The current output end of the above-mentioned automatic controller is respectively connected to the input ends of the first solenoid valve, the second solenoid valve, the third solenoid valve, the fourth solenoid valve, the fifth solenoid valve, the sixth solenoid valve, the seventh solenoid valve, the eighth solenoid valve, the alarm device, the liquid hydrogen pump, and the gaseous hydrogen pump through cables;

[0021] The current input terminals of the automatic controller are respectively connected to the output terminals of the first pressure sensor, the first temperature sensor, the first flow sensor, the second pressure sensor, the second temperature sensor, the second flow sensor, the third pressure sensor, the third temperature sensor, the third flow sensor, the fourth pressure sensor, the fifth pressure sensor, the acoustic flaw detection sensor, and the capacitance liquid level sensor through cables.

[0022] The above-mentioned anti-slosh baffle plates include the first upper baffle plate, the second upper baffle plate, the third upper baffle plate, the first lower baffle plate, the second lower baffle plate, the third lower baffle plate, the first anti-slosh baffle plate, the second anti-slosh baffle plate, the third anti-slosh baffle plate, the fourth anti-slosh baffle plate, the fifth anti-slosh baffle plate, and the sixth anti-slosh baffle plate;

[0023] One ends of the first anti-slosh baffle plate, the second anti-slosh baffle plate, the fifth anti-slosh baffle plate, and the sixth anti-slosh baffle plate are respectively connected to the tank body of the hydrogen storage tank by welding. The first upper baffle plate is connected to the first anti-slosh baffle plate and the second anti-slosh baffle plate by welding. The third upper baffle plate is connected to the fifth anti-slosh baffle plate and the sixth anti-slosh baffle plate by welding. The second upper baffle plate is connected to the third anti-slosh baffle plate and the fourth anti-slosh baffle plate by welding. One ends of the first lower baffle plate, the second lower baffle plate, and the third lower baffle plate are respectively connected to the tank body of the hydrogen storage tank by welding;

[0024] The first upper baffle plate, the second upper baffle plate, and the third upper baffle plate are welded with metal heat conducting rods.

[0025] In the middle section of the above-mentioned cold insulation material module, eight V-shaped support structures are respectively installed at equal intervals along the circumference in the vacuum layer, the phase change material layer, and the insulation layer. Eight V-shaped support structures are also respectively installed in the vacuum layer, the phase change material layer, and the insulation layer on the two domes on both sides of the storage tank; all the support structures are provided with one support point on the inner wall surface of the storage tank and two support points on the outer wall surface.

[0026] The above-mentioned device also includes a first support and a second support, which are installed at the bottom of the cold insulation material module by welding, and the material is selected as a metal material with good compressive capacity;

[0027] The device also includes a capacitance liquid level gauge, a capacitance liquid level sensor, a gas phase thermometer, and a liquid phase thermometer. The capacitance liquid level gauge is used to directly measure the liquid level height of the liquid hydrogen in the liquid hydrogen storage tank. The capacitance liquid level sensor is used to display the liquid level data and transmit the liquid level change of the liquid hydrogen to the automatic controller for analysis. The gas phase thermometer is used to measure the temperature of the hydrogen in the liquid hydrogen storage tank, and the liquid phase thermometer is used to measure the temperature of the liquid hydrogen in the liquid hydrogen storage tank.

[0028] The insulation layer is filled with insulation materials with good insulation effect and low density;

[0029] The wall surface of the hydrogen storage tank body is coated with corrosion-resistant materials, which can effectively weaken the corrosion effect of liquid hydrogen and phase change materials on the wall surface;

[0030] The first dome protection layer and the second dome protection layer are provided with a fireproof layer and an impact-proof layer to reduce the collision of the liquid hydrogen storage tank and play a role in fire prevention at the same time;

[0031] The inner liner material and the outer liner material of the hydrogen storage tank body are made of stainless steel;

[0032] All of the support structures are made of fiberglass, with a hollow structure inside and a certain degree of vacuum maintained, and materials that block radiation and heat conduction and are light in weight are selected;

[0033] The metal heat conduction rod is made of a corrosion-resistant metal with good heat conduction performance;

[0034] The hydrogen fuel cell system has a hydrogen inlet, an oxygen inlet, and a drain outlet, which are used for cooling the aircraft engine and providing domestic water; both the hydrogen inlet section pipeline and the oxygen inlet section adopt curved pipelines.

[0035] The working method of the new multi-layer cold insulation structure liquid hydrogen storage tank device includes a liquid hydrogen combustion process, a gaseous hydrogen power generation process, and an automatic control process;

[0036] The liquid hydrogen combustion process is as follows: The liquid hydrogen inside the hydrogen storage tank body, under the action of the liquid hydrogen pump, flows along the curved liquid hydrogen pipeline through the liquid hydrogen vacuum layer, the liquid hydrogen phase change material layer, and the heat insulation layer, and after flowing out of the storage tank, it is monitored for pressure, temperature, and flow parameters by the second pressure sensor, the second temperature sensor, and the second flow sensor, and then flows to the first end of the fifth solenoid valve. After the liquid hydrogen flows out from the second end of the fifth solenoid valve, it enters the inlet end of the booster vaporizer. Inside the booster vaporizer, the liquid hydrogen is pressurized and vaporized into high-pressure gaseous hydrogen. After the high-pressure gaseous hydrogen flows out from the outlet end of the booster vaporizer, it is monitored for pressure, temperature, and flow parameters by the third pressure sensor, the third temperature sensor, and the third flow sensor, and then flows to the first end of the eighth solenoid valve. After the opening of the eighth solenoid valve is adjusted by the automatic controller, the gaseous hydrogen is introduced into the aircraft engine for combustion;

[0037] The above-mentioned gaseous hydrogen power generation process is as follows: The gaseous hydrogen evaporated above the hydrogen storage tank body is introduced to the outside through the gaseous hydrogen outlet under the action of the heat exchanger. After the gaseous hydrogen flows out through the check valve, it is monitored for pressure, temperature, and flow parameters by the first pressure sensor, the first temperature sensor, and the first flow sensor. A part of it flows to the hydrogen fuel cell system after the opening of the sixth solenoid valve is adjusted, reacts and generates electricity under the action of the oxygen in the oxygen cylinder, and the generated water flows to the living area and cools the aircraft engine; another part flows to the gaseous hydrogen pump after the opening of the seventh solenoid valve is adjusted. The low-pressure hydrogen is pressurized into high-pressure hydrogen in the gaseous hydrogen pump and then flows to the aircraft engine for combustion. Among them: A part of the generated electricity of the hydrogen fuel cell system is used for the gaseous hydrogen pump, and the remaining electricity is used for other facilities of the aircraft; When the gaseous hydrogen is not needed, it can be discharged outside the aircraft through the hydrogen evacuation port.

[0038] The above-mentioned automatic control process is as follows: Liquid hydrogen flows through the second pressure sensor, the second temperature sensor, and the second flow sensor. After the pressure, temperature, and flow parameters are monitored, the opening degree of the fifth solenoid valve is adjusted by the automatic controller to regulate the liquid hydrogen flow rate entering the booster vaporizer.

[0039] Liquid hydrogen flows through the third pressure sensor, the third temperature sensor, and the third flow sensor. After the pressure, temperature, and flow parameters are monitored, the opening degree of the eighth solenoid valve is adjusted by the automatic controller to regulate the gaseous hydrogen flow rate entering the aircraft engine.

[0040] After gaseous hydrogen flows through the first pressure sensor, the first temperature sensor, and the first flow sensor and the pressure, temperature, and flow parameters are monitored, the opening degrees of the sixth solenoid valve and the seventh solenoid valve are adjusted by the automatic controller to regulate the hydrogen gas flow rates entering the hydrogen fuel cell and the hydrogen gas pump respectively.

[0041] The fourth pressure sensor, the fifth pressure sensor, the acoustic flaw detection sensor, the capacitance liquid level sensor, and the alarm device are connected to the automatic controller to monitor the pressure of the vacuum layer, the damage degree of the phase change material layer, the liquid level of liquid hydrogen, and the storage risk of the storage tank respectively.

[0042] The present invention has the following beneficial effects:

[0043] 1. The present invention is provided with three layers of cold insulation materials including a vacuum layer, a phase change material layer, and a thermal insulation layer from the inside out, which reduces the equivalent thermal conductivity, lowers the daily evaporation rate of liquid hydrogen, and reduces the loss of liquid hydrogen during use or transportation.

[0044] 2. The present invention is provided with a V-shaped hollow fiberglass support structure between the three layers of cold insulation materials outside the main body of the hydrogen storage tank, and anti-slosh partitions and liquid hydrogen partition plates are arranged up and down inside, so that the overall pressure-bearing strength of the storage tank is good, the quality is light, and at the same time, the sloshing amplitude of liquid hydrogen in the storage tank during takeoff and landing of the aircraft is effectively weakened, which is beneficial to the flight stability of the aircraft.

[0045] 3. The present invention designs a metal heat conduction rod above the liquid hydrogen, and at the same time adopts a coating with strong corrosion resistance on the storage tank wall surface, effectively solving the problem of uneven temperature inside the storage tank, resulting in a temperature gradient inside the storage tank, increasing the storage efficiency and safety of liquid hydrogen, protecting the materials inside the storage tank from the corrosion of liquid hydrogen, and extending the service life of the storage tank.

[0046] 4. The present invention adds a hydrogen gas pump, so that the pressure of the evaporated hydrogen gas can be directly supplied for engine combustion, and part of the hydrogen gas is used to generate electricity through the fuel cell system or the cold energy Rankine cycle, providing electrical energy for the compressor, reducing the power supply demand for the aircraft, and recycling the evaporated hydrogen gas.

[0047] 5. The present invention uses a capacitive liquid level gauge, an alarm device, and various pressure, temperature, flow sensors, an electric control valve, a compressor, etc., which are connected and controlled through the cables of an automatic controller. The regulation of the valve opening can be realized through the coordinated use of a cut-off valve. The system is safer and more reliable, the control method is intelligent, and the operation efficiency of system pressurization, gasification, etc. is high. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] Figure 1 is a schematic diagram of the whole of the present invention;

[0049] Figure 2 is a schematic diagram of the cooling system of the present invention;

[0050] Figure 3 is Figure 1 a sectional view of the cold insulation structure in

[0051] Figure 4 is Figure 1 a plan view of the support structure in

[0052] Figure 5 is Figure 1 a three-dimensional schematic diagram of a single support structure in

[0053] Figure 6 is Figure 1 a three-dimensional structure schematic diagram of the upper and lower partition plates and the partition plate in

[0054] The accompanying reference numerals are: 1, liquid hydrogen; 2, liquid hydrogen vacuum layer; 3, liquid hydrogen phase change material layer; 4, liquid hydrogen heat preservation layer; 5, first upper partition plate; 6, second upper partition plate; 7, third upper partition plate; 8, first lower partition plate; 9, second lower partition plate; 10, third lower partition plate; 11, first anti-slosh partition plate; 12, second anti-slosh partition plate; 13, third anti-slosh partition plate; 14, fourth anti-slosh partition plate; 15, fifth anti-slosh partition plate; 16, sixth anti-slosh partition plate; 17, metal heat conduction rod; 18, first support; 19, second support; 20, first electromagnetic valve; 21, liquid hydrogen inlet; 22, vacuum pumping device; 23, second electromagnetic valve; 24, fourth pressure sensor; 25, phase change material inlet; 26, third electromagnetic valve; 27, acoustic flaw detection sensor; 28, capacitance liquid level gauge; 29, capacitance liquid level sensor; 30, phase change material outlet; 31, fourth electromagnetic valve; 32, gaseous hydrogen heat exchanger; 33, gaseous hydrogen outlet; 34, liquid hydrogen pump; 35, liquid hydrogen outlet; 36, gas-phase thermometer; 37, liquid-phase thermometer; 38, support structure; 39, check valve; 40, first pressure sensor; 41, first temperature sensor; 42, first flow sensor; 43, hydrogen evacuation port; 44, sixth electromagnetic valve; 45, hydrogen fuel cell system; 46, oxygen cylinder; 47, seventh electromagnetic valve; 48, gaseous hydrogen pump; 49, second pressure sensor; 50, second temperature sensor; 51, second flow sensor; 52, fifth electromagnetic valve; 53, booster vaporizer; 54, third pressure sensor; 55, third temperature sensor; 56, third flow sensor; 57, eighth electromagnetic valve; 58, aircraft engine; 59, automatic controller; 60, first dome protection layer; 61, second dome protection layer; 62, alarm device; 63, fifth pressure sensor; 64, cooling water pump; 65, aircraft hydraulic system; 66, aircraft electrical system; 67, aircraft drain. Detailed implementation manners

[0055] In order to make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0056] Although the steps in the present invention are arranged with reference numerals, they are not used to limit the sequence of steps. Unless the sequence of steps is clearly stated or the execution of a certain step requires other steps as a basis, the relative sequence of steps can be adjusted. It can be understood that the term "and / or" used herein relates to and covers any and all possible combinations of one or more of the associated listed items.

[0057] Please refer to Figure 1, A liquid hydrogen storage device with a multi-layer thermal insulation structure according to the present invention includes liquid hydrogen 1, a liquid hydrogen vacuum layer 2, a liquid hydrogen phase change material layer 3, a liquid hydrogen thermal insulation layer 4, a first upper partition plate 5, a second upper partition plate 6, a third upper partition plate 7, a first lower partition plate 8, a second lower partition plate 9, a third lower partition plate 10, a first anti-slosh partition plate 11, a second anti-slosh partition plate 12, a third anti-slosh partition plate 13, a fourth anti-slosh partition plate 14, a fifth anti-slosh partition plate 15, a sixth anti-slosh partition plate 16, a metal heat conduction rod 17, a first support 18, a second support 19, a first solenoid valve 20, a liquid hydrogen inlet 21, a vacuum pumping port 22, a second solenoid valve 23, a fourth pressure sensor 24, a phase change material inlet 25, a third solenoid valve 26, an ultrasonic flaw detection sensor 27, a capacitance liquid level gauge 28, a capacitance liquid level sensor 29, a phase change material outlet 30, a fourth solenoid valve 31, a gaseous hydrogen heat exchanger 32, a gaseous hydrogen outlet 33, a liquid hydrogen pump 34, a liquid hydrogen outlet 35, a gas-phase thermometer 36, a liquid-phase thermometer 37, first to one hundred and forty-four support structures 38, a check valve 39, a first pressure sensor 40, a first temperature sensor 41, a first flow sensor 42, a hydrogen evacuation port 43, a sixth solenoid valve 44, a hydrogen fuel cell system 45, an oxygen cylinder 46, a seventh solenoid valve 47, a gaseous hydrogen pump 48, a second pressure sensor 49, a second temperature sensor 50, a second flow sensor 51, a fifth solenoid valve 52, a booster vaporizer 53, a third pressure sensor 54, a third temperature sensor 55, a third flow sensor 56, an eighth solenoid valve 57, an aircraft engine 58, an automatic controller 59, a first dome protection layer 60, a second dome protection layer 61, an alarm device 62, a fifth pressure sensor 63, a cooling water pump 64, an aircraft hydraulic system 65, an aircraft electrical system 66, an aircraft drain port 67; It mainly consists of a hydrogen storage tank main body, a cold insulation material device, a support structure device, a liquid hydrogen injection and output device, a vacuum pumping device, and a phase change material injection and discharge device. The present invention innovatively adds a cryogenic phase change material layer in the liquid hydrogen storage tank. By utilizing the characteristics of the phase change material to store cold energy, it solves the problem of high daily evaporation rate of traditional liquid hydrogen storage tanks; upper and lower partition plates and left and right partition plates are arranged inside the liquid hydrogen storage tank, which solves the problem of large-scale sloshing of liquid hydrogen in the storage tank caused by the takeoff and landing of the aircraft; all support structures are made of fiberglass material, and the internal designed cavity also maintains a certain vacuum degree, which solves the defect of easy heat leakage of traditional support structures; a liquid hydrogen pump is provided in the liquid phase inside the storage tank to raise the liquid hydrogen to a certain pressure for engine combustion. In addition, the hydrogen pressure relief port is connected to the hydrogen fuel cell system, which can supply power to the pumps on the aircraft, and the remaining power can supply power to other facilities, and the generated water can be used for cooling the aircraft engine, which solves the problems of insufficient utilization of liquid hydrogen and single use conditions. Therefore, the present invention has the advantages of good cold insulation effect, low daily evaporation rate, good stability, and high energy utilization rate.

[0058] Specifically, the thermal insulation structure is sequentially arranged as a vacuum layer 2, a phase change material layer 3, and a thermal insulation layer 4. The support structure 38 between each layer is connected to the stainless steel layer of the liquid hydrogen storage tank through screws respectively;

[0059] The first end of the gaseous hydrogen outlet 33 is connected to the heat exchanger 32, and the second end is connected to the first end of the check valve 39 through a pipeline. The second end of the check valve 39 is sequentially connected to the first ends of a first pressure sensor 40, a first temperature sensor 41, and a first flow sensor 42 through pipelines. The second end of the first flow sensor 42 is connected to the first end of the hydrogen evacuation port 43. The second end of the hydrogen evacuation port 43 is respectively connected to the first ends of a sixth solenoid valve 44 and a seventh solenoid valve 47 through pipelines. The second end of the sixth solenoid valve 44 is connected to the first end of the hydrogen fuel cell 45 through a pipeline. The second end of the seventh solenoid valve 47 is connected to the first end of the gaseous hydrogen pump 48 through a pipeline. The second end of the hydrogen fuel cell 45 is connected to the oxygen tank 46 through a pipeline, and the third end of the hydrogen fuel cell 45 is connected to the second end of the gaseous hydrogen pump 48 through an electric wire. The third end of the gaseous hydrogen pump 48 is connected to the aircraft engine 58 through a pipeline;

[0060] The first end of the liquid hydrogen outlet 35 is connected to the first end of a second pressure sensor 49 through a pipeline. The second end of the second pressure sensor 49 is sequentially connected to the first ends of a second temperature sensor 50 and a second flow sensor 51 through pipelines. The second end of the second flow sensor 51 is connected to the first end of a fifth solenoid valve 52 through a pipeline. The second end of the fifth solenoid valve 52 is connected to the first end of the booster vaporizer 53 through a pipeline. The second end of the booster vaporizer 53 is sequentially connected to the first ends of a third pressure sensor 54, a third temperature sensor 55, and a third flow sensor 56 through pipelines. The second end of the third flow sensor 56 is connected to the first end of an eighth solenoid valve 57 through a pipeline. The second end of the eighth solenoid valve 57 is connected to the aircraft engine 58 through a pipeline; Please refer to Figure 2 , the cold energy of the booster vaporizer 53 is sent into the engine system 58, hydraulic system 65, and electrical system 66 of the aircraft by the cooling water pump 64 to cool the three systems respectively, realizing the efficient utilization of cold energy. The generated water is discharged out of the aircraft through the aircraft drain port 67.

[0061] The current output terminal of the automatic controller 59 is respectively connected to the input terminals of the first solenoid valve 20, the second solenoid valve 23, the third solenoid valve 26, the fourth solenoid valve 31, the fifth solenoid valve 52, the sixth solenoid valve 44, the seventh solenoid valve 47, the eighth solenoid valve 57, the alarm device 62, the liquid hydrogen pump 34, and the gaseous hydrogen pump 48 through cables. The current input terminal of the automatic controller 59 is respectively connected to the output terminals of the first pressure sensor 40, the first temperature sensor 41, the first flow sensor 42, the second pressure sensor 49, the second temperature sensor 50, the second flow sensor 51, the third pressure sensor 54, the third temperature sensor 55, the third flow sensor 56, the fourth pressure sensor 24, the fifth pressure sensor 63, the acoustic flaw detection sensor 27, and the capacitance liquid level sensor 29 through cables;

[0062] Please refer to Figure 4 , for the support structure of the liquid hydrogen storage tank of the present invention, eight V-shaped support structures 38 are respectively installed at equal circumferential intervals in the vacuum layer 2, the phase change material layer 3, and the thermal insulation material layer 4 in the middle section, with a total of four layers installed. Eight V-shaped support structures 38 are also respectively installed in the vacuum layer 2, the phase change material layer 3, and the thermal insulation material layer 4 on the two side domes of the storage tank. All the support structures 38 have one support point on the inner wall surface of the storage tank and two support points on the outer wall surface. When there is a large pressure difference between the inside of the liquid hydrogen and the outside of the storage tank, it can support the stainless steel wall surface of the storage tank from deforming and has good structural strength;

[0063] The vacuum layer 2 is provided with a vacuum pumping port 22, a second solenoid valve 23, and a fourth pressure sensor 24, which can perform vacuum pumping operations on the vacuum layer 2 of the liquid hydrogen storage tank. The opening degree of the second solenoid valve 23 can be controlled by monitoring the pressure of the fourth pressure sensor 24 by the automatic controller 59 to ensure safety during vacuum pumping;

[0064] The phase change material layer is provided with a phase change material inlet 25, a third solenoid valve 26, a phase change material outlet 30, a fourth solenoid valve 31, and an acoustic flaw detection sensor 27. The opening degree of the third solenoid valve 26 is controlled by monitoring the liquid level of the phase change material by the automatic controller 59, and the corrosion condition of the liquid hydrogen storage tank wall surface by the phase change material is monitored by the acoustic flaw detection sensor 27, which can ensure that the main material of the storage tank is in a safe hydrogen storage state;

[0065] The capacitance liquid level gauge 28 is used to directly measure the liquid level height of the liquid hydrogen in the liquid hydrogen storage tank. The capacitance liquid level sensor 29 facilitates the operator to intuitively view the liquid level data and transmit the liquid level change of the liquid hydrogen to the automatic controller 59 for analysis. The gas phase thermometer 36 is used to measure the temperature of the hydrogen in the liquid hydrogen storage tank, and the liquid phase thermometer 37 is used to measure the temperature of the liquid hydrogen in the liquid hydrogen storage tank.

[0066] The thermal insulation layer 4 is filled with a thermal insulation material with good thermal insulation effect and low density, which can achieve a better cold storage effect;

[0067] The wall surfaces of the liquid hydrogen storage tank are coated with corrosion-resistant materials, which can effectively weaken the corrosion of the liquid hydrogen and phase change materials on the wall surfaces;

[0068] The first dome protection layer 60 and the second dome protection layer 61 of the liquid hydrogen storage tank are respectively provided with a fireproof layer and an anti-impact layer, which can reduce the collision of the liquid hydrogen storage tank and play a role in fire prevention at the same time;

[0069] The anti-slosh baffles in the liquid hydrogen storage tank, one end of the first anti-slosh baffle 11, the second anti-slosh baffle 12, the fifth anti-slosh baffle 15, and the sixth anti-slosh baffle 16 are respectively connected to the tank body of the storage tank by welding. The first upper baffle 5 is connected to the first anti-slosh baffle 11 and the second anti-slosh baffle 12 by welding. The third upper baffle 7 is connected to the fifth anti-slosh baffle 15 and the sixth anti-slosh baffle 16 by welding. The second upper baffle 6 is connected to the third anti-slosh baffle 13 and the fourth anti-slosh baffle 14 by welding. One end of the first lower baffle 8, the second lower baffle 9, and the third lower baffle 10 are respectively connected to the tank body of the storage tank by welding;

[0070] The inner tank material and outer tank material of the liquid hydrogen storage tank are made of stainless steel with strong corrosion resistance and good strength at low temperatures. The support structure is all made of fiberglass, with a hollow structure inside and a certain vacuum degree maintained. The thermal insulation material is selected to block radiation and heat conduction and is lightweight. The support structure is installed at the bottom of the liquid hydrogen storage tank by welding, and the material is selected as a metal material with good compressive capacity. The metal heat conducting rod 17 is connected to the first upper baffle 5, the second upper baffle 6, and the third upper baffle 7 by welding, and the material is selected as a corrosion-resistant metal with good thermal conductivity;

[0071] The hydrogen fuel cell system 45 has a hydrogen inlet, an oxygen inlet, and a drain outlet, and can cool down the aircraft engine and provide domestic water;

[0072] The pipeline of the hydrogen inlet section and the hydrogen inlet section of the liquid hydrogen storage tank both adopt bent pipelines;

[0073] An alarm device 62 and a fifth pressure sensor 63 are connected to the outside of the dome of the liquid hydrogen storage tank by screws, and can flash red lights and emit sounds for alarm;

[0074] The working method of a liquid hydrogen storage device with a multi-layer thermal insulation structure according to the present invention includes a vacuum pumping method, a phase change material filling method, a thermal insulation material installation method, a liquid hydrogen filling method, a liquid hydrogen combustion process, a gaseous hydrogen power generation process, and an automatic control process of the liquid hydrogen storage tank device:

[0075] 1. Vacuum pumping method: First, before pumping vacuum, check the cleanliness of the interior and exterior of the storage tank, as well as the air extraction port and connectors, remove dust, dirt, and grease from all vacuum layers, and ensure that all seals such as O-rings and gaskets are in good condition without aging or damage; Second, according to the capacity and vacuum requirements of the storage tank, select a suitable pump, first use a mechanical pump for preliminary vacuum pumping, and then use a high-vacuum pump for deep vacuum pumping; Third, after reaching the predetermined vacuum level, seal the air extraction port to ensure that no gas enters the vacuum layer again.

[0076] 2. Phase change material filling method: First, according to the temperature requirements and application needs of the storage tank, select a suitable phase change material; Second, ensure that the area of the phase change material layer in the storage tank is clean and free of impurities; Clean the inner wall of the storage tank and related components to avoid contamination and affecting the material properties; Check the tightness of the storage tank and connectors to ensure that the insulation layer does not leak during the filling process; Third, for solid PCM at room temperature, heat it to the molten state for filling in the storage tank; For liquid PCM at room temperature, fill it directly.

[0077] 3. Thermal insulation material installation method: First, select a thermal insulation material with a low thermal conductivity, stable at extremely low temperatures, and not brittle or ineffective; Second, before installing the thermal insulation material, ensure that the surface of the storage tank is clean, free of impurities such as dust and grease; Check whether the surface of the storage tank is smooth to ensure that there is no damage or corrosion, prepare tools and materials, and ensure that the size and quantity of the thermal insulation material meet the requirements of the storage tank; Third, install a layer of basic thermal insulation material first, usually a relatively thick foam or thermal insulation blanket, cut the basic layer material according to the size of the storage tank to ensure that it covers the entire surface and maintains a uniform thickness, and use a suitable adhesive or fixing clip to firmly fix the basic layer material on the surface of the storage tank; Fourth, cut the main thermal insulation materials such as vacuum insulation panels and foams into appropriate blocks according to the shape and size of the storage tank, lay the cut thermal insulation materials on the basic layer one by one to ensure seamless coverage of the entire surface, and for joints and connections, use sealant or special tape for sealing to prevent heat conduction and entry of external moisture; Fifth, install an outer protective material such as aluminum foil or metal shell to protect the thermal insulation layer, fix the protective layer material outside the thermal insulation layer to ensure that there is no gap between the protective layer and the thermal insulation layer.

[0078] 4. Liquid hydrogen filling method: First, ensure that the storage tank has no leaks, cracks or other damages. Check whether the insulation layer of the storage tank is intact, confirm that the vacuum layer of the storage tank maintains the specified vacuum degree, and ensure good insulation performance. Check the filling pipeline and connectors to ensure there is no damage or wear. Ensure that the liquid hydrogen filling pump functions normally. Ensure good ventilation in the filling area and follow all safety regulations to prevent explosion risks caused by hydrogen leakage. Second, slowly introduce coolants such as nitrogen or helium into the storage tank, gradually reduce the temperature of the storage tank to be close to the temperature of liquid hydrogen. At the same time, the air in the storage tank can be discharged to avoid sudden temperature changes caused by direct entry of liquid hydrogen into the storage tank, which may cause the air in the storage tank to condense and affect hydrogen filling. Third, start the liquid hydrogen filling pump, pump the liquid hydrogen out of the storage tank and transport it into the storage tank. The filling process is carried out slowly, controlling the flow rate and pressure of the liquid hydrogen, and real-time monitoring of the pressure, temperature and flow rate during the filling process to ensure that the liquid hydrogen remains within the safe temperature and pressure range during filling. Fourth, observe the reading of the capacitive level gauge. When the storage tank reaches the predetermined filling volume, stop the filling pump, close the filling valve, disconnect the filling pipeline, and seal the filling port of the storage tank to ensure that all connections are sealed well.

[0079] 5. Liquid hydrogen combustion process: The liquid hydrogen in the storage tank, under the action of the liquid hydrogen pump, flows along the liquid hydrogen pipeline in a curved manner through the vacuum layer, phase change material layer, thermal insulation layer, and then flows out of the storage tank. After being monitored for pressure, temperature, and flow rate parameters by the second pressure sensor, second temperature sensor, and second flow sensor, it flows to the first end of the fifth solenoid valve. The liquid hydrogen flows out from the second end of the fifth solenoid valve and enters the inlet end of the booster vaporizer. In the booster vaporizer, the liquid hydrogen is pressurized and vaporized into high-pressure gaseous hydrogen. The high-pressure gaseous hydrogen flows out from the outlet end of the booster vaporizer and is monitored for pressure, temperature, and flow rate parameters by the third pressure sensor, third temperature sensor, and third flow sensor, and then flows to the first end of the eighth solenoid valve. After the opening of the eighth solenoid valve is adjusted by the automatic controller, the gaseous hydrogen is introduced into the aircraft engine for combustion.

[0080] 6. Gaseous hydrogen power generation process: The gaseous hydrogen evaporated above the liquid hydrogen storage tank is introduced to the outside through the gaseous hydrogen pipeline under the action of the heat exchanger. After flowing out through the check valve, the gaseous hydrogen is monitored for pressure, temperature, and flow rate parameters by the first pressure sensor, first temperature sensor, and first flow sensor. Part of it flows to the hydrogen fuel cell system after the opening of the sixth solenoid valve is adjusted, reacts with the oxygen in the oxygen cylinder to generate electricity, and the generated water flows to the living area and cools the aircraft engine. The other part flows to the gaseous hydrogen pump after the opening of the seventh solenoid valve is adjusted. The low-pressure hydrogen is pressurized into high-pressure hydrogen in the gaseous hydrogen pump and then flows to the aircraft engine for combustion. Among them: part of the power generated by the hydrogen fuel cell is used for the gaseous hydrogen pump, and the remaining power is used for other facilities of the aircraft. When the gaseous hydrogen is not needed, it can be discharged outside the aircraft through the hydrogen evacuation port.

[0081] 7. Automatic control process: After the liquid hydrogen flows through the second pressure sensor, the second temperature sensor, and the second flow sensor to be monitored for pressure, temperature, and flow parameters, the automatic controller adjusts the opening degree of the second solenoid valve to regulate the liquid hydrogen flow rate into the booster vaporizer; after the liquid hydrogen flows through the third pressure sensor, the third temperature sensor, and the third flow sensor to be monitored for pressure, temperature, and flow parameters, the automatic controller adjusts the opening degree of the eighth solenoid valve to regulate the gaseous hydrogen flow rate into the aircraft engine; after the gaseous hydrogen flows through the first pressure sensor, the first temperature sensor, and the first flow sensor to be monitored for pressure, temperature, and flow parameters, the automatic controller adjusts the opening degrees of the sixth solenoid valve and the seventh solenoid valve to regulate the hydrogen flow rates into the hydrogen fuel cell and the gaseous hydrogen pump respectively; in addition, the fourth pressure sensor, the fifth pressure sensor, the acoustic flaw detection sensor, the capacitance liquid level sensor, and the alarm device are also connected to the automatic controller, which can monitor the pressure of the vacuum layer, the damage degree of the phase change material layer, the liquid level of the liquid hydrogen, the storage risk of the storage tank, and other states respectively.

[0082] For those skilled in the art, it is obvious that the present invention is not limited to the details of the above exemplary embodiments, and without departing from the spirit or basic characteristics of the present invention, the present invention can be implemented in other specific forms. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present invention. Any reference signs in the claims should not be construed as limiting the claimed invention.

[0083] In addition, it should be understood that although this specification is described according to embodiments, not every embodiment only contains an independent technical solution. This narrative way of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A new type of multi-layer cold-insulation structure liquid hydrogen storage tank device, characterized in that: It includes a hydrogen storage tank body, a cold insulation material module, a support structure module, a liquid hydrogen injection and output module, a vacuum module, a phase change material injection and discharge module, and an automatic controller (59); The hydrogen storage tank body includes liquid hydrogen (1), a gas-hydrogen heat exchanger (32), and a gas-hydrogen outlet (33), and an anti-sway baffle is provided inside; the gas-hydrogen heat exchanger (32) is connected to the gas-hydrogen outlet (33), and the gas-hydrogen outlet (33) is connected to the gas-hydrogen power generation branch; The cold insulation material module is divided into a middle section, a first dome protective layer (60) and a second dome protective layer (61), each of which comprises a liquid hydrogen vacuum layer (2), a liquid hydrogen phase change material layer (3) and a heat insulation layer (4) which are sequentially wrapped around the outside of the hydrogen storage tank body, and the outside of the second dome protective layer (61) is connected to an alarm device (62) and a fifth pressure sensor (63) by screws; The support structure module includes a plurality of support structures (38) for supporting each layer in the cold insulation material module, and is connected to the stainless steel layer of the liquid hydrogen storage tank; The liquid hydrogen injection output module is arranged on the first dome protective layer (60), comprises a first solenoid valve (20), a liquid hydrogen inlet (21), a liquid hydrogen pump (34), and a liquid hydrogen outlet (35), and the output end is connected to the liquid hydrogen combustion branch; The vacuum module is arranged in the liquid hydrogen vacuum layer (2), and comprises a vacuum port (22), a second electromagnetic valve (23), and a fourth pressure sensor (24); the automatic controller (59) monitors the pressure of the fourth pressure sensor (24) and controls the opening of the second electromagnetic valve (23) to ensure safety during vacuuming; The phase change material injection and discharge module is arranged on the liquid hydrogen phase change material layer (3), and comprises a phase change material inlet (25), a third electromagnetic valve (26), an acoustic wave flaw detection sensor (27), a phase change material outlet (30), and a fourth electromagnetic valve (31). The liquid level of the phase change material is monitored by an automatic controller (59) to control the opening of the third electromagnetic valve (26), and the corrosion of the phase change material on the wall of the liquid hydrogen storage tank is monitored by the acoustic wave flaw detection sensor (27) to ensure that the main material of the storage tank is in a safe hydrogen storage state.

2. According to claim 1, a novel multi-layer cold-insulation structure liquid hydrogen storage tank device is characterized in that: The gas-hydrogen power generation branch comprises a check valve (39), a first pressure sensor (40), a first temperature sensor (41), a first flow sensor (42), a hydrogen exhaust port (43), a sixth solenoid valve (44), a hydrogen fuel cell system (45), an oxygen cylinder (46), a seventh solenoid valve (47), and a gas-hydrogen pump (48); The first end of the gas hydrogen outlet (33) is connected to the heat exchanger (32), and the second end is connected to the first end of the check valve (39) through a pipeline. The second end of the check valve (39) is connected to the first end of the first pressure sensor (40), the first temperature sensor (41), and the first end of the first flow sensor (42) in sequence through a pipeline. The second end of the first flow sensor (42) is connected to the first end of the hydrogen exhaust port (43). The second end of the hydrogen exhaust port (43) is connected to the first end of the sixth solenoid valve (44) and the first end of the seventh solenoid valve (47) through pipelines. The second end of the sixth solenoid valve (44) is connected to the first end of the hydrogen fuel cell (45) through a pipeline. The second end of the seventh solenoid valve (47) is connected to the first end of the gas hydrogen pump (48) through a pipeline. The second end of the hydrogen fuel cell (45) is connected to the oxygen tank (46) through a pipeline. The third end of the hydrogen fuel cell (45) is connected to the second end of the gas hydrogen pump (48) through an electric wire. The third end of the gas hydrogen pump (48) is connected to the aircraft engine (58) through a pipeline.

3. According to claim 2, a novel multi-layer cold-insulation structure liquid hydrogen storage tank device is characterized in that: The liquid hydrogen combustion branch comprises a second pressure sensor (49), a second temperature sensor (50), a second flow sensor (51), a fifth solenoid valve (52), a supercharger gasifier (53), a third pressure sensor (54), a third temperature sensor (55), a third flow sensor (56), an eighth solenoid valve (57), and an aircraft engine (58) which are connected in sequence; The first end of the liquid hydrogen outlet (35) is connected to the first end of the second pressure sensor (49) through a pipeline, the second end of the second pressure sensor (49) is connected to the second temperature sensor (50) and the first end of the second flow sensor (51) in sequence through a pipeline, the second end of the second flow sensor (51) is connected to the first end of the fifth solenoid valve (52) through a pipeline, the second end of the fifth solenoid valve (52) is connected to the first end of the supercharged gasifier (53) through a pipeline, the second end of the supercharged gasifier (53) is connected to the third pressure sensor (54), the third temperature sensor (55), and the first end of the third flow sensor (56) in sequence through a pipeline, the second end of the third flow sensor (56) is connected to the first end of the eighth solenoid valve (57) through a pipeline, and the second end of the eighth solenoid valve (57) is connected to the aircraft engine (58) through a pipeline; The cooling energy of the supercharged gasifier (53) is delivered to the aircraft engine (58), the hydraulic system (65) and the electrical system (66) by a cooling water pump (64), respectively cooling the three systems, thereby realizing efficient utilization of the cooling energy, and the generated water is discharged outside the aircraft through a drain port (67) of the aircraft.

4. A novel multi-layer cold-insulation structure liquid hydrogen storage tank device according to claim 3, characterized in that: The current output end of the automatic controller (59) is respectively connected to the input ends of the first solenoid valve (20), the second solenoid valve (23), the third solenoid valve (26), the fourth solenoid valve (31), the fifth solenoid valve (52), the sixth solenoid valve (44), the seventh solenoid valve (47), the eighth solenoid valve (57), the alarm device (62), the liquid hydrogen pump (34), and the gas hydrogen pump (48) through cables; The current input end of the automatic controller (59) is respectively connected to the output ends of the first pressure sensor (40), the first temperature sensor (41), the first flow sensor (42), the second pressure sensor (49), the second temperature sensor (50), the second flow sensor (51), the third pressure sensor (54), the third temperature sensor (55), the third flow sensor (56), the fourth pressure sensor (24), the fifth pressure sensor (63), the acoustic flaw detection sensor (27), and the capacitive liquid level sensor (29) through cables.

5. According to claim 1, a novel multi-layer cold-insulation structure liquid hydrogen storage tank device is characterized in that: The anti-sway baffle comprises a first upper baffle (5), a second upper baffle (6), a third upper baffle (7), a first lower baffle (8), a second lower baffle (9), a third lower baffle (10), a first anti-sway baffle (11), a second anti-sway baffle (12), a third anti-sway baffle (13), a fourth anti-sway baffle (14), a fifth anti-sway baffle (15), and a sixth anti-sway baffle (16); One end of the first anti-sway baffle (11), the second anti-sway baffle (12), the fifth anti-sway baffle (15), and the sixth anti-sway baffle (16) are respectively connected to the tank body of the hydrogen storage tank by welding; the first upper baffle (5) is connected to the first anti-sway baffle (11) and the second anti-sway baffle (12) by welding; the third upper baffle (7) is connected to the fifth anti-sway baffle (15) and the sixth anti-sway baffle (16) by welding; the second upper baffle (6) is connected to the third anti-sway baffle (13) and the fourth anti-sway baffle (14) by welding; and one end of the first lower baffle (8), the second lower baffle (9), and the third lower baffle (10) are respectively connected to the tank body of the hydrogen storage tank by welding; The first upper baffle plate (5), the second upper baffle plate (6) and the third upper baffle plate (7) are welded with metal heat-conducting rods (17).

6. According to claim 1, a novel multi-layer cold-insulation structure liquid hydrogen storage tank device is characterized in that: In the middle section of the cold-insulating material module, eight V-shaped support structures (38) are installed at equal intervals along the circumference of the vacuum layer (2), the phase-change material layer (3), and the thermal insulation layer (4); and eight V-shaped support structures (38) are also installed at the vacuum layer (2), the phase-change material layer (3), and the thermal insulation layer (4) of the domes on both sides of the storage tank; all the support structures (38) are provided with one support point on the inner wall surface of the storage tank and two support points on the outer wall surface.

7. A novel multi-layer cold-insulation structure liquid hydrogen storage tank device and its working method according to claim 1, characterized in that: The device also includes a first support (18) and a second support (19), which are installed on the bottom of the cold insulation material module by welding, and the material is a metal material with good pressure resistance; The device further comprises a capacitance liquid level meter (28), a capacitance liquid level sensor (29), a gas phase thermometer (36) and a liquid phase thermometer (37), wherein the capacitance liquid level meter (28) is used to directly measure the liquid level height of liquid hydrogen in the liquid hydrogen storage tank, the capacitance liquid level sensor (29) is used to display liquid level data and transmit the liquid level change of liquid hydrogen to the automatic controller (59) for analysis, the gas phase thermometer (36) is used to measure the temperature of hydrogen in the liquid hydrogen storage tank, and the liquid phase thermometer (37) is used to measure the temperature of liquid hydrogen in the liquid hydrogen storage tank; The thermal insulation layer (4) is filled with a thermal insulation material with good thermal insulation effect and low density; The wall surface of the hydrogen storage tank body is coated with corrosion-resistant material, which can effectively weaken the corrosion effect of liquid hydrogen and phase change material on the wall surface; The first dome protective layer (60) and the second dome protective layer (61) are provided with a fireproof layer and an impact-proof layer to reduce the collision of the liquid hydrogen storage tank and play a role in fire prevention; The inner liner material and the outer liner material of the hydrogen storage tank body are made of stainless steel; The support structure (38) is entirely made of glass fiber reinforced plastics, has a hollow interior, and maintains a certain degree of vacuum. The material used is radiation-blocking and heat-conducting and lightweight. The metal heat-conducting rod (17) is made of corrosion-resistant metal with good heat-conducting performance; The hydrogen fuel cell system (45) has a hydrogen inlet, an oxygen inlet, and a water outlet for cooling the aircraft engine and providing domestic water; the hydrogen inlet section pipeline and the oxygen inlet section both use curved pipelines.

8. The working method of the novel multi-layer cold-insulation structure liquid hydrogen storage tank device according to any one of claims 1 to 7, characterized in that: Including liquid hydrogen combustion process, gas hydrogen power generation process and automatic control process; The liquid hydrogen combustion process is as follows: the liquid hydrogen (1) inside the hydrogen storage tank body flows along the liquid hydrogen pipeline under the action of the liquid hydrogen pump (34), passes through the liquid hydrogen vacuum layer (2), the liquid hydrogen phase change material layer (3), the insulation layer (4), flows to the outside of the storage tank, and is monitored by the second pressure sensor (49), the second temperature sensor (50), and the second flow sensor (51) for pressure, temperature, and flow parameters, and then flows to the first end of the fifth solenoid valve (52). The liquid hydrogen flows out from the second end of the fifth solenoid valve (52) and enters the booster. At the inlet end of the compression gasifier (53), liquid hydrogen is pressurized and gasified into high-pressure gaseous hydrogen in the supercharged gasifier (53). The high-pressure gaseous hydrogen flows out from the outlet end of the supercharged gasifier (53) and is monitored by a third pressure sensor (54), a third temperature sensor (55), and a third flow sensor (56) for pressure, temperature, and flow parameters, and then flows to the first end of an eighth solenoid valve (57). After the opening of the eighth solenoid valve (57) is adjusted by an automatic controller (59), the gaseous hydrogen is introduced into an aircraft engine (58) for combustion.

9. The working method according to claim 8, characterized in that: The gas-hydrogen power generation process is as follows: the gas-hydrogen evaporated above the hydrogen storage tank body is introduced to the outside through the gas-hydrogen outlet (33) under the action of the heat exchanger (32); after the gas-hydrogen flows out through the check valve (39), the pressure, temperature and flow parameters are monitored by the first pressure sensor (40), the first temperature sensor (41) and the first flow sensor (42); a part of the gas-hydrogen flows to the hydrogen fuel cell system (45) after the opening is adjusted by the sixth solenoid valve (44); the gas-hydrogen reacts with the oxygen in the oxygen cylinder (46) to generate electricity; the generated water flows to the living area and cools the aircraft engine; the other part of the gas-hydrogen flows to the gas-hydrogen pump (48) after the opening is adjusted by the seventh solenoid valve (47); the low-pressure hydrogen is pressurized into high-pressure hydrogen in the gas-hydrogen pump (48) and flows to the aircraft engine (58) for combustion; wherein: a part of the power generation of the hydrogen fuel cell system (45) is used for the gas-hydrogen pump (48), and the remaining power is used for other facilities of the aircraft; when the gas-hydrogen is not needed, it can be discharged outside the aircraft through the hydrogen exhaust port (43).

10. The liquid hydrogen storage device with a multi-layer thermal insulation structure according to claim 8, characterized in that: The automatic control process is as follows: after the liquid hydrogen (1) flows through the second pressure sensor (49), the second temperature sensor (50), and the second flow sensor (51), the pressure, temperature, and flow parameters are monitored, and then the opening of the fifth solenoid valve (52) is adjusted by the automatic controller to adjust the flow of liquid hydrogen entering the boost gasifier (53); The liquid hydrogen flows through a third pressure sensor (54), a third temperature sensor (55), and a third flow sensor (56) to monitor the pressure, temperature, and flow parameters, and then the automatic controller adjusts the opening of the eighth solenoid valve (57) to adjust the flow of gaseous hydrogen entering the aircraft engine (58); After the gaseous hydrogen flows through the first pressure sensor (40), the first temperature sensor (41), and the first flow sensor (42), the pressure, temperature, and flow parameters are monitored, and the openings of the sixth solenoid valve (44) and the seventh solenoid valve (47) are adjusted by the automatic controller to adjust the flow rates of hydrogen entering the hydrogen fuel cell (45) and the gaseous hydrogen pump (48), respectively; The fourth pressure sensor (24), the fifth pressure sensor (63), the acoustic wave flaw detection sensor (27), the capacitive liquid level sensor (29), and the alarm device (62) are connected to the automatic controller (59) to respectively monitor the pressure of the vacuum layer, the damage degree of the phase change material layer, the liquid level of the liquid hydrogen, and the storage risk of the storage tank.

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