Hydrogen and oxygen purification method and system of aviation integrated reversible closed hydrogen and oxygen fuel cell

Abstract

The invention relates to the technical field of fuel cells, and discloses a hydrogen and oxygen purification method and system for an aviation integrated reversible closed hydrogen and oxygen fuel cell, and the purification method specifically comprises the following steps: collecting operation condition parameters of an integrated reversible closed hydrogen and oxygen fuel cell system and flight condition parameters of an aircraft; determining an oxygen storage concentration upper limit of the hydrogen storage device and a hydrogen storage concentration upper limit of the oxygen storage device; then identifying the current operation mode of the hydrogen-oxygen fuel cell system, and determining the target operation time of each hydrogen-oxygen purification device of the hydrogen-oxygen fuel cell system in the current operation mode in combination with the operation condition parameters and the state parameters of the hydrogen storage device and the oxygen storage device; and finally, according to the current operation mode of the hydrogen-oxygen fuel cell system, controlling the corresponding hydrogen-oxygen purification device to operate according to the corresponding target operation time. According to the invention, the blank of the hydrogen-oxygen purification technology of the integrated reversible closed hydrogen-oxygen fuel cell system in the aviation field is filled, and an efficient, safe and reliable energy system support is provided for aviation aircrafts.

Description

Technical Field

[0001] This invention relates to the field of fuel cell technology, and more specifically to a method and system for purifying hydrogen and oxygen in an integrated reversible closed-loop hydrogen-oxygen fuel cell for aviation. Background Technology

[0002] In a closed-loop integrated reversible fuel cell system, hydrogen, oxygen, and water are stored in their respective containers without mass exchange with the environment, achieving a charging and discharging function similar to a secondary battery. However, after prolonged operation, due to factors such as operating mode switching, hydrogen and oxygen evolution from water dissolution, and membrane permeation, hydrogen and oxygen become mixed, leading to a decrease in the purity of the gases in the hydrogen and oxygen storage devices. This results in risks such as energy loss and potential deflagration.

[0003] Currently, the technologies related to integrated reversible closed-loop fuel cell systems mainly focus on system composition, control during power generation and electrolysis, and water management. No hydrogen and oxygen purification solutions have been found applicable to integrated reversible closed-loop hydrogen-oxygen fuel cell systems. Furthermore, existing general hydrogen and oxygen removal methods suffer from problems such as large size, high energy consumption, and unsuitability for aviation scenarios and integrated reversible closed-loop hydrogen-oxygen fuel cell systems, making them unsuitable for reference or direct utilization.

[0004] Therefore, it is necessary to propose a hydrogen and oxygen purification scheme for an integrated reversible closed-loop hydrogen-oxygen fuel cell suitable for aviation scenarios. Summary of the Invention

[0005] In view of the problems and shortcomings of the existing technology, this invention proposes a method and system for purifying hydrogen and oxygen in an integrated reversible closed-loop hydrogen-oxygen fuel cell for aviation.

[0006] To achieve the above-mentioned objectives, the technical solution of the present invention is as follows: This invention discloses a method for purifying hydrogen and oxygen in an integrated reversible closed-loop hydrogen-oxygen fuel cell for aviation, the method comprising the following steps: Step S1. Obtain the operating condition parameters of the airborne integrated reversible closed hydrogen-oxygen fuel cell system and the flight condition parameters of the aircraft. Based on the operating condition parameters and the flight condition parameters, determine the upper limit of oxygen concentration of the airborne hydrogen storage device and the upper limit of hydrogen concentration of the airborne oxygen storage device, respectively. Step S2. Identify the current operating mode of the airborne integrated reversible closed-loop hydrogen-oxygen fuel cell system. Based on the operating parameters of the airborne integrated reversible closed-loop hydrogen-oxygen fuel cell system, the flight parameters of the aircraft, and the status parameters of the hydrogen storage device and the oxygen storage device, determine the target operating time of the hydrogen-oxygen purification device under the current operating mode of the airborne integrated reversible closed-loop hydrogen-oxygen fuel cell system. Step S3. Control the hydrogen-oxygen purification device to operate according to the target operating time corresponding to the current operating mode of the aircraft.

[0007] Preferably, the hydrogen-oxygen fuel cell system operates in three modes: electrolysis, standby, and power generation. The target operating time of the hydrogen-oxygen purification device differs depending on the operating mode, as detailed below: (I) When the onboard integrated reversible closed-loop hydrogen-oxygen fuel cell system is in electrolysis mode, the target operating time of the first hydrogen-oxygen purification device at the hydrogen storage device's gas supply port is: t e1 The target operating time of the second hydrogen-oxygen purification unit at the oxygen storage unit's gas supply port is [number] seconds. t e2 The running time for the two targets is calculated in seconds as follows: Equation (1); Equation (2); In the formula, and The test margin coefficient, To address the operational pressures of an onboard integrated reversible closed-loop hydrogen-oxygen fuel cell system. For the theoretical mixing volume of oxygen, This represents the theoretical mixing volume of hydrogen. The operating temperature for an airborne integrated reversible closed-loop hydrogen-oxygen fuel cell system. This represents the minimum hydrogen electrolysis flow rate for an integrated airborne reversible closed-loop hydrogen-oxygen fuel cell system. This represents the minimum oxygen electrolysis flow rate for an integrated airborne reversible closed-loop hydrogen-oxygen fuel cell system. It is the gas constant; (II) When the onboard integrated reversible closed-loop hydrogen-oxygen fuel cell system is in power generation mode, the target operating time of the first hydrogen-oxygen purification device at the hydrogen storage device's gas supply port and the second hydrogen-oxygen purification device at the oxygen storage device's gas supply port is 1. t f seconds; among which, Equation (6); In the formula, For correction factor, S H The mesh coverage area of ​​the first hydrogen-oxygen purification unit within the hydrogen storage device. S O The mesh coverage area of ​​the second hydrogen-oxygen purification device within the oxygen storage unit; H PH The heat of fusion of water under gas pressure in a hydrogen storage device. H PO The heat of fusion of water under gas pressure in an oxygen storage device;Q H This refers to the heating power of the heating wire in the first hydrogen-oxygen purification device. Q O The heating power of the heating wire in the second hydrogen-oxygen purification device; (III) When the integrated reversible closed-loop hydrogen-oxygen fuel cell system is in standby mode, If the oxygen concentration sensor reading in the onboard hydrogen storage device is > n c2 The target operating time of the first hydrogen-oxygen purification unit at the gas supply port of the hydrogen storage device is... t d Second; If the reading of the hydrogen concentration sensor in the onboard oxygen storage device is > n c1 The target operating time for the second hydrogen-oxygen purification unit at the oxygen storage unit's gas supply port is also... t d seconds; among which, Equation (5); For correction factor, n O This represents the molar concentration of oxygen, an impurity gas, in the hydrogen storage device. n H This represents the molar concentration of hydrogen, an impurity gas, in the oxygen storage device. This refers to the volume of the hydrogen storage device; This refers to the volume of the oxygen storage device; m O This represents the molar mass of oxygen, an impurity gas, in the hydrogen storage device. m H This represents the molar mass of hydrogen, an impurity gas, in the oxygen storage device. h H The height of the hydrogen storage device; h O The height of the oxygen storage device; k Boltzmann's constant; T H This refers to the gas temperature inside the hydrogen storage device. T O The temperature of the gas inside the oxygen storage device; w H The hydrogen-oxygen catalytic reaction rate of the first hydrogen-oxygen purification unit at the gas supply port of the hydrogen storage device; w O The hydrogen-oxygen catalytic reaction rate of the second hydrogen-oxygen purification device at the oxygen storage device's gas supply port; n c1 This represents the upper limit of hydrogen concentration in the oxygen storage device. n c2 This represents the upper limit of oxygen concentration for hydrogen storage devices.

[0008] Preferably, the upper limit of hydrogen concentration in the oxygen storage device is calculated as follows: Equation (3); In the formula, The test margin coefficient, , The coefficient representing the influence of hydrogen storage pressure. , The influence coefficient of hydrogen storage at the flight altitude of the aircraft. P O To store pressure for the oxygen storage device, H The flight altitude of the aircraft. This is the lower limit for hydrogen deflagration.

[0009] Preferably, the upper limit of oxygen concentration in the hydrogen storage device is calculated as follows: Equation (4); In the formula, The experimental margin influence coefficient is... , The factor representing the influence of oxygen storage pressure is... , The oxygen storage influence coefficient at the aircraft's flight altitude. P H To store pressure for hydrogen storage devices, H The flight altitude of the aircraft. This is the lower limit for oxygen deflagration.

[0010] Preferably, the flight conditions of the aircraft include the aircraft's flight altitude.

[0011] Preferably, the hydrogen concentration sensor is arranged in the gas phase region at the top of the oxygen storage device.

[0012] Preferably, the oxygen concentration sensor is arranged in the gas phase region at the top of the hydrogen storage device.

[0013] Based on the same inventive concept, another aspect of this invention discloses a hydrogen-oxygen purification system for an integrated reversible closed-loop hydrogen-oxygen fuel cell for aviation. This system is used to implement the aforementioned hydrogen-oxygen purification method for the integrated reversible closed-loop hydrogen-oxygen fuel cell. The architecture of the hydrogen-oxygen purification system is as follows: it includes a controller, a first hydrogen-oxygen purification device disposed at the front end of the gas supply port of a hydrogen storage device, a second hydrogen-oxygen purification device disposed at the front end of the gas supply port of an oxygen storage device, an oxygen concentration sensor and a first pressure sensor disposed within the hydrogen storage device, and a hydrogen concentration sensor and a second pressure sensor disposed within the oxygen storage device. The oxygen concentration sensor, hydrogen concentration sensor, first pressure sensor, and second pressure sensor are respectively communicatively connected to the controller. The oxygen concentration sensor is used to monitor the oxygen concentration inside the hydrogen storage device; The hydrogen concentration sensor is used to monitor the hydrogen concentration in the oxygen storage device. The first pressure sensor is used to monitor the gas pressure inside the hydrogen storage device; The second pressure sensor is used to monitor the gas pressure inside the oxygen storage device; The controller receives data collected by the oxygen concentration sensor, hydrogen concentration sensor, first pressure sensor, and second pressure sensor, as well as the flight condition parameters of the aircraft and the operating condition parameters of the integrated reversible closed-loop hydrogen-oxygen fuel cell system. Based on the above parameters, it identifies the current operating mode of the aircraft and determines the target operating time corresponding to the first and second hydrogen-oxygen purification devices under the current operating mode of the integrated reversible closed-loop hydrogen-oxygen fuel cell system. It then controls the first and second hydrogen-oxygen purification devices to operate according to the target operating time corresponding to the current operating mode of the aircraft.

[0014] Preferably, the first and second hydrogen-oxygen purification devices have the same structure, including an annular metal frame, with filaments having heating and catalytic functions arranged in an interlaced mesh pattern in the inner ring of the annular metal frame. Preferably, the wire consists of inner and outer sides, with the inner layer being a heating wire with a circular cross-section and the outer layer being a porous medium catalytic layer wrapped around the surface of the heating wire, wherein the porous medium catalytic layer is doped with a catalyst.

[0015] Preferably, the first and second hydrogen-oxygen purification devices are each equipped with a temperature sensor.

[0016] The beneficial effects of this invention are: 1. This invention proposes a hydrogen and oxygen purification method for an airborne integrated reversible closed-loop hydrogen-oxygen fuel cell system in the aviation field. It can effectively improve the gas purity in the airborne hydrogen and oxygen storage devices, reduce the energy loss and explosion risk caused by gas mixing after long-term operation of the integrated reversible closed-loop hydrogen-oxygen fuel cell system, and improve performance stability and operational safety. 2. This invention comprehensively considers factors such as the operating conditions of the hydrogen-oxygen fuel cell system itself, the flight conditions of the aircraft, the status of the hydrogen and oxygen storage devices, theoretical fuel risks, and experimental conditions to derive the upper limit of hydrogen concentration for the oxygen storage device and the upper limit of oxygen concentration for the hydrogen storage device. The judgment conditions are more reasonable and conducive to improving the safety of the integrated reversible closed-loop hydrogen-oxygen fuel cell system.

[0017] 3. This invention integrates the flight conditions of the aircraft with the structural performance parameters and operating conditions of the integrated reversible closed-loop hydrogen-oxygen fuel cell system to obtain the target operating time of the hydrogen-oxygen purification device under each operating mode. Under the premise of meeting system safety, it balances the contradiction between hydrogen-oxygen fuel utilization rate and heating power loss, reduces the total energy loss of the hydrogen-oxygen fuel cell system, and improves the system energy conversion efficiency.

[0018] 4. The present invention provides a hydrogen and oxygen purification device with electric heating function at the supply port of the hydrogen and oxygen storage device. By heating according to the set steps, the problems of water freezing and blockage caused by low temperature in the high-altitude environment and reduction of system circulating water can be solved, the accumulation of solid water at the bottle mouth can be reduced, the risk of gas supply blockage can be reduced, the utilization rate of water in the system can be improved, and the system can operate efficiently, safely and reliably during flight in all airspace.

[0019] 5. The hydrogen-oxygen purification device of the present invention is installed at the front end of the gas supply port of the hydrogen storage device and the oxygen storage device. It does not require modification of the original pipelines, valves and other components, and can be directly integrated into the existing integrated system, resulting in low modification costs. Furthermore, the purification device adopts a ring-shaped metal skeleton and interlaced mesh wire design, which makes the overall size small and the weight light, meeting the requirements of lightweight and miniaturization in the aerospace field. Attached Figure Description

[0020] The foregoing and hereinafter detailed description of the invention becomes clearer when read in conjunction with the following drawings, in which: Figure 1 This is a flowchart of the method of the present invention; Figure 2 This is a schematic diagram of the hydrogen storage device of the present invention; Figure 3 This is a schematic diagram of the oxygen storage device of the present invention; Figure 4 This is a schematic diagram of the hydrogen and oxygen purification device of the present invention. In the picture: 1. Oxygen concentration sensor; 2. Hydrogen concentration sensor; 3. First hydrogen and oxygen purification device; 4. Second hydrogen and oxygen purification device; 5. Heating wire; 6. Porous medium catalyst layer; 7. Temperature sensor. Detailed Implementation

[0021] To enable those skilled in the art to better understand the technical solutions of this invention, specific embodiments will be used to further illustrate the technical solutions for achieving the objectives of this invention. It should be noted that the technical solutions claimed by this invention include, but are not limited to, the following embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without inventive effort should fall within the scope of protection of this invention. An integrated reversible hydrogen-oxygen fuel cell system is an energy system that uses hydrogen, oxygen, and water as fuel and working medium, generating electricity and electrolyzing within the same proton exchange membrane fuel cell stack. If a closed-loop configuration is adopted where the working fluids (hydrogen, oxygen, and water) do not exchange mass with the environment, the integrated reversible closed-loop hydrogen-oxygen fuel cell can be considered a type of secondary battery (lithium battery, lead-acid battery) with charge-discharge energy. Integrated reversible closed-loop hydrogen-oxygen fuel cells feature high energy density, low-temperature resistance, long cycle life, and independence from the environment. They can replace traditional secondary batteries such as lithium batteries and lead-acid batteries as primary energy storage devices, and have broad application prospects in underwater, aviation, and aerospace fields.

[0022] In the aviation field, airborne integrated reversible hydrogen-oxygen fuel cells can serve as the main energy storage device for aircraft such as pure electric drones, solar-powered drones, and solar-powered airships, improving the flight time, range, and environmental adaptability of aircraft, extending flight altitude, and providing efficient energy supply for electric aircraft in low, medium, and high airspace.

[0023] Currently, the integrated reversible closed-loop hydrogen-oxygen fuel cell for aviation adopts a multi-mode, integrated design scheme, which allows hydrogen, oxygen, and water to share some pipelines, control valves, and sensors, and achieves multi-mode switching of power generation and electrolysis functions through special control strategies. Compared with the separate configuration of hydrogen, oxygen, and water, the integrated reversible hydrogen-oxygen fuel cell system has fewer components, lighter weight, and smaller volume, which significantly improves the overall power density and energy density of the battery system. However, the integrated design also produces the following problems: (1) During the switching between power generation and electrolysis modes, some hydrogen or oxygen will remain in the shared pipelines, valves, separators, heat exchangers, and other equipment. In the electrolysis mode, the hydrogen and oxygen generated by water electrolysis are stored in the hydrogen storage device and oxygen storage device, respectively. The shared equipment causes hydrogen and oxygen to mix with each other, which reduces the concentration of hydrogen and oxygen in the hydrogen storage device and oxygen storage device. Moreover, with the increase of charge and discharge times, the concentration of hydrogen and oxygen in the hydrogen storage device and oxygen storage device gradually decreases, resulting in a reduction in the actual stored energy of the system, and even the risk of deflagration. (2) Aircraft are in a low-temperature environment at high altitudes. After repeated charging and discharging and long-term operation at high altitudes, water vapor may accumulate and frost in the hydrogen and oxygen storage devices, resulting in a reduction of available water and energy storage in the system, and also increasing the risk of blockage in the hydrogen and oxygen storage devices.

[0024] To address the issues of hydrogen-oxygen mixing and water accumulation during continuous operation of airborne integrated reversible closed-loop hydrogen-oxygen fuel cells used in aircraft, this invention proposes a hydrogen-oxygen purification method and system for airborne integrated reversible hydrogen-oxygen fuel cells. This method can increase the concentration of hydrogen and oxygen in the hydrogen and oxygen storage devices respectively, reduce water accumulation in the devices, lower the risk of gas supply blockage, and enable the battery system to operate efficiently, safely, and reliably in all airspace.

[0025] This embodiment first discloses a method for purifying hydrogen and oxygen in an integrated reversible closed-loop hydrogen-oxygen fuel cell system for aviation. The integrated reversible closed-loop hydrogen-oxygen fuel cell is used as an energy storage system for a high-altitude, long-endurance solar-powered unmanned aerial vehicle (UAV). The structural schematic diagrams of its hydrogen storage device and oxygen storage device are shown below. Figure 2 and Figure 3 As shown, the hydrogen storage device is a vertical cylindrical gas cylinder with an aluminum alloy inner liner and a composite material winding. The maximum working pressure is 35 MPa. The cylinder is placed vertically with the opening facing downwards. Oxygen concentration sensor 1 is located at the top of the hydrogen storage device (top gas phase region). Its range is 12%, its measurement accuracy is ±0.5%FS, and its response time is 1 second. It measures the oxygen concentration n in the top region of the hydrogen storage device in real time. O The oxygen storage device is a vertical cylindrical gas cylinder with an aluminum alloy inner liner and composite material winding. The maximum hydrogen storage pressure is 35 MPa. The cylinder is placed vertically with the opening facing downwards. Hydrogen concentration sensor 2 is located at the top of the hydrogen storage device (top gas phase region). Its range is 8%, its measurement accuracy is ±0.5%FS, and its response time is 1 second. It is used to measure the hydrogen concentration n in the top region of the oxygen storage device in real time. H .

[0026] A first hydrogen-oxygen purification device 3 and a second hydrogen-oxygen purification device 4 are respectively installed at the gas supply ports of the hydrogen storage device and the oxygen storage device (the first hydrogen-oxygen purification device 3 is located at the gas supply port of the hydrogen storage device, and the second hydrogen-oxygen purification device 4 is located at the gas supply port of the oxygen storage device). The two hydrogen-oxygen purification devices have the same structure, as shown below. Figure 4 As shown, the entire device is a rigid annular metal ring, inside which is a catalytic and heating mesh. The rigid metal ring is essentially a ring-shaped metal skeleton, with the inner ring containing a crisscrossing mesh of heating and catalytic wires. Furthermore, the wires have a circular cross-section and a double-layer structure. The inner layer is a circular heating wire 5, and the outer layer of the heating wire 5 is covered with a porous media catalytic layer 6, which is doped with catalysts such as palladium and platinum. Simultaneously, the hydrogen-oxygen purification device is equipped with a temperature sensor 7 (e.g., ...). Figure 4 As shown, it is mounted on a metal ring and used to monitor the temperature of the hydrogen-oxygen purification device. The controlled temperature of the hydrogen-oxygen purification device is 150-250℃.

[0027] The specific method for purifying hydrogen and oxygen for the aforementioned integrated reversible hydrogen-oxygen fuel cell is as follows: (1) Collect the operating condition parameters of the airborne integrated reversible closed hydrogen-oxygen fuel cell system and the flight condition parameters of the aircraft. Based on the above operating condition parameters, determine the upper limit of oxygen concentration of the airborne hydrogen storage device and the upper limit of hydrogen concentration of the airborne oxygen storage device.

[0028] Data from the aircraft's altitude sensor indicates that the current flight altitude of the high-altitude, long-endurance solar-powered drone is [missing information]. HData from the first pressure sensor inside the hydrogen storage device mounted on the drone indicates that the gas pressure inside the device is [value missing]. P H And the gas pressure inside the oxygen storage device can be determined from the data of the second pressure sensor inside the oxygen storage device. P O Furthermore, the operating pressure within the entire integrated aerospace reversible closed-loop hydrogen-oxygen fuel cell system is... P .

[0029] Based on the above parameters, the calculation methods for the upper limit of oxygen concentration in a hydrogen storage device and the upper limit of hydrogen concentration in an oxygen storage device are as follows: Upper limit of hydrogen concentration in oxygen storage devices n c1 The calculation method is as follows: Equation (3); in, It is the experimental margin factor (generally related to parameters such as catalyst performance, heating temperature of the hydrogen-oxygen purification device, and flow rate of hydrogen or oxygen). , This is the pressure influence coefficient (the influence coefficient of gas pressure inside the oxygen storage device on the upper limit of hydrogen storage concentration, which can be determined through experiments). , The influence coefficient of drone flight altitude. P O To store pressure for the oxygen storage device, H This is the current flight altitude of the aircraft. The lower limit of hydrogen deflagration is typically taken as 4%; Furthermore, the upper limit of oxygen concentration in hydrogen storage devices. n c2 The calculation method is as follows: Equation (4); in, It is the experimental margin factor (generally related to parameters such as catalyst performance, heating temperature of the hydrogen-oxygen purification device, and flow rate of hydrogen or oxygen). , This is the pressure influence coefficient (the influence coefficient of gas pressure inside the hydrogen storage device on the upper limit of oxygen storage concentration, which can be determined through experiments). , The influence coefficient of drone flight altitude. P H To store pressure for hydrogen storage devices, The lower limit of oxygen deflagration is usually taken as 6%.

[0030] (2) Identify the current operating mode of the airborne integrated reversible closed hydrogen-oxygen fuel cell system on the aircraft, and then determine the target operating time of the first hydrogen-oxygen purification device 3 and the second hydrogen-oxygen purification device 4 under the current operating mode based on the operating condition parameters of the airborne integrated reversible closed hydrogen-oxygen fuel cell system and the status parameters of the hydrogen storage device and the oxygen storage device. The airborne integrated reversible closed-loop hydrogen-oxygen fuel cell system operates in three modes: power generation, electrolysis, and standby. Based on each operating mode, the hydrogen-oxygen purification unit has a corresponding target operating time. The following section details how to calculate the target operating time of the hydrogen-oxygen purification unit under each operating mode.

[0031] In this invention, the target operating time of the hydrogen-oxygen purification device under each operating mode is calculated using the ideal gas assumption.

[0032] (a) When the integrated reversible closed-loop hydrogen-oxygen fuel cell system is in electrolysis mode, the target operating time of the first hydrogen-oxygen purification device 3 at the hydrogen storage device's gas supply port is: t e1 Seconds, the first hydrogen-oxygen purification unit 3 started operating. t e1 After a few seconds, excess mixed oxygen is removed from the hydrogen storage device. t e1 The calculation method is as follows: Equation (1); in, It is the experimental margin factor (generally related to parameters such as catalyst performance, heating temperature of the hydrogen-oxygen purification device, and flow rate of hydrogen or oxygen). To address the operational pressures of integrated reversible closed-loop hydrogen-oxygen fuel cell systems in aviation, This represents the theoretical mixing volume of oxygen (which is structure-dependent). The operating temperature for an integrated reversible closed-loop hydrogen-oxygen fuel cell system for aviation. To achieve the minimum hydrogen electrolysis flow rate for an integrated reversible closed-loop hydrogen-oxygen fuel cell system for aviation. It is the gas constant; The target operating time of the second hydrogen-oxygen purification unit 4 at the oxygen storage unit's gas supply port is: t e2 Seconds, the second hydrogen-oxygen purification unit 4 is running. t e2 After a few seconds, remove any excess mixed hydrogen from the oxygen storage device. t e2 The calculation method is as follows: Equation (2); in, It is the experimental margin factor (generally related to parameters such as catalyst performance, heating temperature of the hydrogen-oxygen purification device, and flow rate of hydrogen or oxygen). This represents the theoretical mixing volume of hydrogen (which is structure-dependent). The minimum oxygen electrolysis flow rate for an integrated reversible closed-loop hydrogen-oxygen fuel cell system for aviation.

[0033] (b) When the onboard integrated reversible closed-loop hydrogen-oxygen fuel cell system is in standby mode, and the readings of hydrogen concentration sensor 2 and oxygen concentration sensor 1 meet the following conditions, the target operating time of the first hydrogen-oxygen purification device 3 at the hydrogen storage device's gas supply port and the target operating time of the second hydrogen-oxygen purification device 4 at the oxygen storage device's gas supply port are both... t d seconds, of which, If the reading of hydrogen concentration sensor 2 in the oxygen storage device is > n c1 The target operating time of the second hydrogen-oxygen purification device 4 at the oxygen storage device's gas supply port is... t d Second; If the reading of oxygen concentration sensor 1 in the hydrogen storage device is > n c2 The target operating time of the first hydrogen-oxygen purification unit 3 at the gas supply port of the hydrogen storage device is: t d Second; In this invention, t d The structure and condition of the gas cylinder determine the effect, taking into account factors such as molecular weight differences, concentration diffusion, and the catalytic performance of the catalyst within the hydrogen-oxygen purification device. t d The calculation method is as follows: Equation (5); The correction factor was obtained through experimental determination. n O This represents the molar concentration of oxygen, an impurity gas, in the hydrogen storage device. n H This represents the molar concentration of hydrogen, an impurity gas, in the oxygen storage device. This refers to the volume of the hydrogen storage device; This refers to the volume of the oxygen storage device; m O This represents the molar mass of oxygen, an impurity gas, in the hydrogen storage device. m H This represents the molar mass of hydrogen, an impurity gas, in the oxygen storage device. h H The height of the hydrogen storage device; h O The height of the oxygen storage device; kBoltzmann's constant; T H This refers to the gas temperature inside the hydrogen storage device. T O The temperature of the gas inside the oxygen storage device; w H The hydrogen-oxygen catalytic reaction rate of the first hydrogen-oxygen purification device 3 at the gas supply port of the hydrogen storage device; w O The hydrogen-oxygen catalytic reaction rate of the second hydrogen-oxygen purification device 4 at the gas supply port of the oxygen storage device.

[0034] In this invention, for a hydrogen storage device, the impurity gas is oxygen mixed in the gas cylinder, and for an oxygen storage device, the impurity gas is hydrogen mixed in the gas cylinder.

[0035] In the above formula (5), the relevant parameters of the hydrogen storage device and the oxygen storage device are substituted into the calculation, and then the calculated values ​​of the hydrogen storage device and the oxygen storage device are compared. The maximum value of the two is multiplied by the correction factor. As .

[0036] It is understandable that if the readings of the oxygen storage device or the corresponding sensors within the oxygen storage device do not meet the conditions, the corresponding hydrogen and oxygen purification device will not operate.

[0037] (c) When the integrated reversible closed-loop hydrogen-oxygen fuel cell system is in power generation mode, the operating time of the first hydrogen-oxygen purification device 3 at the hydrogen storage device's gas supply port and the target operating time of the second hydrogen-oxygen purification device 4 at the oxygen storage device's gas supply port are both... t f Second, t f The calculation method is as follows: Equation (6); In the formula, The correction factor was obtained through experimental determination. S H The mesh coverage area of ​​the first hydrogen-oxygen purification device 3 within the hydrogen storage device; S O The mesh coverage area of ​​the second hydrogen-oxygen purification device 4 within the oxygen storage device; H PH The heat of fusion of water under the pressure of the hydrogen storage device cylinder. H PO The heat of fusion of water under pressure in the oxygen storage device cylinder; Q H This refers to the heating power of the heating wire 5 in the first hydrogen and oxygen purification device 3. Q O This refers to the heating power of the heating wire 5 in the second hydrogen-oxygen purification device 4.

[0038] Similarly, for the above formula (6), the relevant parameters of the hydrogen storage device and the oxygen storage device are substituted into the formula for calculation. The calculated values ​​of the hydrogen storage device and the oxygen storage device are compared, and the maximum value is multiplied by the correction factor. As .

[0039] (3) Finally, based on the current operating mode of the aviation integrated reversible closed hydrogen-oxygen fuel cell system, control the corresponding hydrogen-oxygen purification device to operate for the corresponding target operating time for the corresponding duration.

[0040] In this invention, it should be noted that for hydrogen storage devices and oxygen storage devices, the gas supply port of the gas cylinder is both the gas inlet and the gas outlet, and the gas enters and exits through the same port.

[0041] It is understood that the operating parameters of the aviation integrated reversible closed hydrogen-oxygen fuel cell system mentioned in this invention are usually parameters such as the operating pressure, operating temperature, minimum electrolytic hydrogen flow rate, and minimum electrolytic oxygen flow rate within the system; the flight operating parameters of the aircraft are usually the flight altitude of the aircraft; and the status parameters of the hydrogen storage device and the oxygen storage device are generally data such as the gas temperature and pressure inside the gas cylinder.

[0042] Based on the same inventive concept, this embodiment also discloses a hydrogen-oxygen purification system for an integrated reversible closed-loop hydrogen-oxygen fuel cell system for aviation. The hydrogen-oxygen purification system is used to implement the aforementioned hydrogen-oxygen purification method. The system's architecture specifically includes a controller, a first hydrogen-oxygen purification device 3, a second hydrogen-oxygen purification device 4, an oxygen concentration sensor 1, a hydrogen concentration sensor 2, a first pressure sensor, and a second pressure sensor. The oxygen concentration sensor 1, hydrogen concentration sensor 2, first pressure sensor, and second pressure sensor are respectively communicatively connected to the controller. The first hydrogen-oxygen purification device 3 is located at the front end of the gas supply port of the hydrogen storage device and is used to remove excess oxygen mixed in the hydrogen storage device. The second hydrogen-oxygen purification device 4 is located at the front end of the oxygen storage device's gas supply port and is used to remove excess hydrogen mixed in the oxygen storage device. The oxygen concentration sensor 1 is installed inside the hydrogen storage device to monitor and collect the concentration of oxygen mixed in the hydrogen storage device. The hydrogen concentration sensor 2 is installed inside the oxygen storage device and is used to monitor and collect the concentration of hydrogen mixed in the oxygen storage device. The first pressure sensor is installed inside the hydrogen storage device to monitor and collect the gas pressure inside the hydrogen storage device. The second pressure sensor is installed inside the hydrogen storage device to monitor and collect the gas pressure inside the oxygen storage device; The controller receives data collected by oxygen concentration sensor 1, hydrogen concentration sensor 2, first pressure sensor and second pressure sensor, as well as the flight condition parameters of the aircraft and the operating condition parameters of the aviation integrated reversible closed hydrogen-oxygen fuel cell system. Then, it identifies the current operating mode of the hydrogen-oxygen fuel cell system and determines the target operating time corresponding to the first hydrogen-oxygen purification device 3 and the second hydrogen-oxygen purification device 4 under the current operating mode of the hydrogen-oxygen fuel cell system based on the above parameters. Finally, it controls the first hydrogen-oxygen purification device 3 and the second hydrogen-oxygen purification device 4 to operate according to the target operating time corresponding to the current operating mode of the aircraft.

[0043] Preferably, the first hydrogen-oxygen purification device 3 and the second hydrogen-oxygen purification device 4 are respectively provided with temperature sensors, which are communicatively connected to the controller and used to transmit the collected temperature data to the controller.

[0044] Furthermore, this embodiment also provides a computer device, which includes a processor, an input device, an output device, and a memory, all interconnected. The memory stores a computer program, which includes program instructions, and the processor is configured to invoke the program instructions to execute the steps described in the above embodiment.

[0045] Furthermore, another aspect of this embodiment provides a computer-readable storage medium storing a computer program, the computer program including program instructions that, when executed by a processor, cause the processor to perform the steps described above.

[0046] In this embodiment, the processor can be a central processing unit (CPU). The processor can also be other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, or combinations of the above types of chips.

[0047] Memory, as a non-transitory computer-readable storage medium, can be used to store non-transitory software programs, non-transitory computer-executable programs, and units, such as the program units corresponding to the above-described method embodiments of the present invention. The processor executes various functional applications and data processing of the processor by running the non-transitory software programs, instructions, and modules stored in the memory, thereby implementing the methods described in the above-described method embodiments.

[0048] The memory may include a program storage area and a data storage area. The program storage area may store the operating system and applications required for at least one function; the data storage area may store data created by the processor, etc. Furthermore, the memory may include high-speed random access memory and non-transitory memory, such as at least one disk storage device, flash memory device, or other non-transitory solid-state storage device. In some embodiments, the memory may optionally include memory remotely located relative to the processor, which can be connected to the processor via a network. Examples of such networks include, but are not limited to, the Internet, corporate intranets, local area networks, mobile communication networks, and combinations thereof.

[0049] The one or more units are stored in the memory and, when executed by the processor, perform the methods described in the above embodiments.

[0050] Those skilled in the art will understand that embodiments of the present invention can be provided as methods, systems, or computer program products. Therefore, the present invention can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects.

[0051] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A method for purifying hydrogen and oxygen in an integrated reversible closed-loop hydrogen-oxygen fuel cell for aviation, characterized in that, Includes the following steps: Step S1. Obtain the operating condition parameters of the airborne integrated reversible closed hydrogen-oxygen fuel cell system and the flight condition parameters of the aircraft. Based on the operating condition parameters and the flight condition parameters, determine the upper limit of the oxygen storage concentration of the hydrogen storage device and the upper limit of the hydrogen storage concentration of the airborne oxygen storage device, respectively. Step S2. Identify the current operating mode of the airborne integrated reversible closed-loop hydrogen-oxygen fuel cell system, and then determine the target operating time of the hydrogen-oxygen purification device under the current operating mode of the airborne integrated reversible closed-loop hydrogen-oxygen fuel cell system based on the operating condition parameters of the airborne integrated reversible closed-loop hydrogen-oxygen fuel cell system, the flight condition parameters of the aircraft, and the status parameters of the hydrogen storage device and the oxygen storage device. Step S3. Control the hydrogen-oxygen purification device to operate according to the target operating time corresponding to the current operating mode of the aircraft.

2. The method for purifying hydrogen and oxygen in an integrated reversible closed-loop hydrogen-oxygen fuel cell according to claim 1, characterized in that, When the onboard integrated reversible closed-loop hydrogen-oxygen fuel cell system is in electrolysis mode, the target operating time of the first hydrogen-oxygen purification device at the hydrogen storage device's gas supply port is: t e1 The target operating time of the second hydrogen-oxygen purification unit at the oxygen storage unit's gas supply port is [number] seconds. t e2 seconds; among which, Equation (1); Equation (2); In the formula, and The test margin coefficient, To address the operational pressures of an airborne integrated reversible closed-loop hydrogen-oxygen fuel cell system. For the theoretical mixing volume of oxygen, This represents the theoretical mixing volume of hydrogen. The operating temperature for an airborne integrated reversible closed-loop hydrogen-oxygen fuel cell system. This represents the minimum hydrogen electrolysis flow rate for an integrated airborne reversible closed-loop hydrogen-oxygen fuel cell system. This represents the minimum oxygen electrolysis flow rate for an integrated airborne reversible closed-loop hydrogen-oxygen fuel cell system. is the gas constant.

3. The method for purifying hydrogen and oxygen in an integrated reversible closed-loop hydrogen-oxygen fuel cell according to claim 1, characterized in that, When the onboard integrated reversible closed-loop hydrogen-oxygen fuel cell system is in power generation mode, the target operating time of the first hydrogen-oxygen purification device at the hydrogen storage device's gas supply port and the second hydrogen-oxygen purification device at the oxygen storage device's gas supply port is [missing information]. t f seconds; among which, Equation (6); In the formula, For correction factor, S H The mesh coverage area of ​​the first hydrogen-oxygen purification unit within the hydrogen storage device. S O The mesh coverage area of ​​the second hydrogen-oxygen purification device within the oxygen storage unit; H PH The heat of fusion of water under gas pressure in a hydrogen storage device. H PO The heat of fusion of water under gas pressure in an oxygen storage device; Q H This refers to the heating power of the heating wire in the first hydrogen-oxygen purification device. Q O This refers to the heating power of the heating wire in the second hydrogen-oxygen purification device.

4. The method for purifying hydrogen and oxygen in an integrated reversible closed-loop hydrogen-oxygen fuel cell according to claim 1, characterized in that, When the integrated reversible closed-loop hydrogen-oxygen fuel cell system is in standby mode If the oxygen concentration sensor reading in the onboard hydrogen storage device is > n c2 The target operating time of the first hydrogen-oxygen purification unit at the gas supply port of the hydrogen storage device is... t d Second; If the reading of the hydrogen concentration sensor in the onboard oxygen storage device is > n c1 The target operating time of the second hydrogen-oxygen purification unit at the oxygen storage unit's gas supply port is... t d seconds; among which, Equation (5); in, For correction factor, n O This represents the molar concentration of oxygen, an impurity gas, in the hydrogen storage device. n H This represents the molar concentration of hydrogen, an impurity gas, in the oxygen storage device. This refers to the volume of the hydrogen storage device; This refers to the volume of the oxygen storage device; m O This represents the molar mass of oxygen, an impurity gas, in the hydrogen storage device. m H This represents the molar mass of hydrogen, an impurity gas, in the oxygen storage device. h H The height of the hydrogen storage device; h O The height of the oxygen storage device; k Boltzmann's constant; T H This refers to the gas temperature inside the hydrogen storage device. T O The temperature of the gas inside the oxygen storage device; w H The hydrogen-oxygen catalytic reaction rate of the first hydrogen-oxygen purification unit at the gas supply port of the hydrogen storage device; w O The hydrogen-oxygen catalytic reaction rate of the second hydrogen-oxygen purification device at the oxygen storage device's gas supply port; n c1 This represents the upper limit of hydrogen concentration in the oxygen storage device. n c2 This represents the upper limit of oxygen concentration for hydrogen storage devices.

5. The method for purifying hydrogen and oxygen in an integrated reversible closed-loop hydrogen-oxygen fuel cell according to claim 1, characterized in that, The calculation method for the upper limit of hydrogen concentration in an oxygen storage device is as follows: Equation (3); In the formula, n c1 This represents the upper limit of hydrogen concentration in the oxygen storage device. The test margin coefficient, , The coefficient representing the influence of hydrogen storage pressure. , The hydrogen storage influence coefficient at the flight altitude of the aircraft. P O To store pressure for the oxygen storage device, H The flight altitude of the aircraft. This is the lower limit for hydrogen deflagration.

6. The method for purifying hydrogen and oxygen in an integrated reversible closed-loop hydrogen-oxygen fuel cell according to claim 1, characterized in that, The calculation method for the upper limit of oxygen concentration in a hydrogen storage device is as follows: Equation (4); In the formula, n c2 This represents the upper limit of oxygen concentration for hydrogen storage devices. The experimental margin influence coefficient is... , The factor representing the influence of oxygen storage pressure is... , The oxygen storage influence coefficient at the aircraft's flight altitude. P H To store pressure for hydrogen storage devices, H The flight altitude of the aircraft. This is the lower limit for oxygen deflagration.

7. The method for purifying hydrogen and oxygen in an integrated reversible closed-loop hydrogen-oxygen fuel cell according to claim 1, characterized in that, The flight conditions of the aircraft include its flight altitude.

8. The method for purifying hydrogen and oxygen in an integrated reversible closed-loop hydrogen-oxygen fuel cell according to claim 4, characterized in that, The hydrogen concentration sensor is located in the gas phase region at the top of the oxygen storage device.

9. The method for purifying hydrogen and oxygen in an integrated reversible closed-loop hydrogen-oxygen fuel cell according to claim 4, characterized in that, The oxygen concentration sensor is located in the gas phase region at the top of the hydrogen storage device.

10. A hydrogen-oxygen purification system for an integrated reversible closed-loop hydrogen-oxygen fuel cell, characterized in that, The hydrogen-oxygen purification system of the aerospace-integrated reversible closed-loop hydrogen-oxygen fuel cell is used to implement the hydrogen-oxygen purification method of the aerospace-integrated reversible closed-loop hydrogen-oxygen fuel cell as described in any one of claims 1-9, comprising: a controller, a first hydrogen-oxygen purification device disposed at the front end of the gas supply port of the hydrogen storage device, a second hydrogen-oxygen purification device disposed at the front end of the gas supply port of the oxygen storage device, an oxygen concentration sensor and a first pressure sensor disposed in the hydrogen storage device, and a hydrogen concentration sensor and a second pressure sensor disposed in the oxygen storage device; wherein the oxygen concentration sensor, hydrogen concentration sensor, first pressure sensor and second pressure sensor are respectively communicatively connected to the controller; wherein... The oxygen concentration sensor is used to monitor the oxygen concentration inside the hydrogen storage device; The hydrogen concentration sensor is used to monitor the hydrogen concentration in the oxygen storage device. The first pressure sensor is used to monitor the gas pressure inside the hydrogen storage device; The second pressure sensor is used to monitor the gas pressure inside the oxygen storage device; The controller receives data collected by the oxygen concentration sensor, hydrogen concentration sensor, first pressure sensor, and second pressure sensor, as well as the flight condition parameters of the aircraft and the operating condition parameters of the integrated reversible closed-loop hydrogen-oxygen fuel cell system. Based on the above parameters, it identifies the current operating mode of the aircraft and determines the target operating time corresponding to the first and second hydrogen-oxygen purification devices under the current operating mode of the integrated reversible closed-loop hydrogen-oxygen fuel cell system. It then controls the first and second hydrogen-oxygen purification devices to operate according to the target operating time corresponding to the current operating mode of the aircraft.

11. The hydrogen-oxygen purification system for an integrated reversible closed-loop hydrogen-oxygen fuel cell according to claim 10, characterized in that, The first and second hydrogen-oxygen purification devices have the same structure, including a ring-shaped metal frame, with filaments having heating and catalytic functions arranged in an interlaced mesh pattern in the inner ring of the ring-shaped metal frame.

12. The hydrogen-oxygen purification system for an integrated reversible closed-loop hydrogen-oxygen fuel cell according to claim 11, characterized in that, The wire consists of inner and outer sides. The inner layer is a heating wire with a circular cross-section, and the outer layer is a porous medium catalytic layer wrapped around the surface of the heating wire. The porous medium catalytic layer is doped with a catalyst.

13. The hydrogen-oxygen purification system for an integrated reversible closed-loop hydrogen-oxygen fuel cell according to claim 10, characterized in that, The first and second hydrogen-oxygen purification devices are each equipped with a temperature sensor.

Images