Method, device and computer equipment for operating evaluation of an aircraft fuel cell

Abstract

The application relates to an aviation fuel cell operation evaluation method, device and computer equipment. The method comprises the following steps: obtaining flight environment information, flight power demand information and aviation fuel cell auxiliary information, thereby identifying aviation fuel cell working condition operation boundary information; based on the working condition operation boundary information, identifying an extreme / conventional working condition operation range of the aviation fuel cell, so as to construct an aviation fuel cell simulation operation strategy; obtaining simulation operation results of each simulation operation strategy, a low-dimensional fuel cell model and an auxiliary model of the aviation fuel cell, thereby constructing an aviation fuel cell model; based on target operation condition information, the target operation results of the aviation fuel cell model are simulated through the aviation fuel cell model, thereby determining target cell control information of the aviation fuel cell. The method can improve the identification accuracy of the fuel cell control strategy facing variable environments.

Description

Technical Field

[0001] This application relates to the field of fuel cell technology, and in particular to an operational evaluation method, apparatus, and computer equipment for aviation fuel cells. Background Technology

[0002] Proton exchange membrane fuel cells (PEMFCs) are electrochemical power sources with high energy conversion efficiency and zero pollutant emissions. Their basic working principle involves the catalytic reaction of hydrogen and oxygen to produce water. The energy released in this reaction is primarily converted into usable electrical energy, with a small portion being converted into waste heat. As a highly efficient and pollution-free next-generation power generation technology, PEMFCs have been widely applied in new energy transportation and green stationary power generation, showing great promise. Developing fuel cell power systems that can adapt to drastic environmental changes is a crucial step towards the maturity of fuel cell technology and a necessary prerequisite for its further growth in the broader transportation sector. Therefore, how to control fuel cell systems is currently a key research focus.

[0003] Existing fuel cell system control strategies are primarily designed and optimized for ground-based operating environments, neglecting the potentially drastic environmental changes that may occur in aviation scenarios. Due to the unique characteristics of the aviation environment, including high altitude, low temperature, and air pressure variations, and the fact that the actual control process of the fuel cell system cannot be directly obtained, existing methods for developing fuel cell control strategies for variable environments remain immature. Summary of the Invention

[0004] Therefore, it is necessary to provide an operational evaluation method, apparatus, computer equipment, computer-readable storage medium, and computer program product for aviation fuel cells to address the aforementioned technical problems.

[0005] In a first aspect, this application provides a method for evaluating the operation of an aviation fuel cell. The method includes:

[0006] The system acquires flight environment information, flight power demand information, and auxiliary component information of the aviation fuel cell, and identifies the operating boundary information of the aviation fuel cell based on the flight environment information, flight power demand information, and auxiliary component information of the aviation fuel cell.

[0007] Based on the operating condition boundary information, the extreme operating condition range and the normal operating condition range of the aviation fuel cell are identified, and a simulation operation strategy for the aviation fuel cell is constructed based on the extreme operating condition range and the normal operating condition range.

[0008] The simulation results obtained by the staff based on the simulation operation strategies are obtained through the simulation operation of the aviation fuel cell, the low-dimensional fuel cell model of the aviation fuel cell, and the auxiliary component model of the aviation fuel cell. Based on the low-dimensional fuel cell model and the auxiliary component model, the initial aviation fuel cell model of the aviation fuel cell is constructed.

[0009] Based on the simulation results, parameter fitting processing is performed on each model parameter in the initial aviation fuel cell model to obtain the aviation fuel cell model, and based on each simulation result, the target operating condition information is determined.

[0010] Based on the target operating condition information, the control process of the aviation fuel cell under the target operating condition information is simulated through the aviation fuel cell model to obtain the target operating result of the aviation fuel cell model. Based on the target operating result, the target battery control information of the aviation fuel cell is determined.

[0011] Optionally, identifying the operating boundary information of the aviation fuel cell based on the flight environment information, the flight power demand information, and the auxiliary component information of the aviation fuel cell includes:

[0012] Based on the flight environment information, environmental data of different environment types are identified, and the environmental data of each environment type are divided and processed according to different altitude ranges to obtain environmental data groups corresponding to each altitude range;

[0013] Based on the flight power demand information, the power constraint information of the aviation fuel cell corresponding to different flight states and the heat dissipation constraint information corresponding to each flight state are identified. Based on the auxiliary component information of the aviation fuel cell, the airflow control information of the battery auxiliary components under different altitude conditions is identified.

[0014] Based on the power constraint information and heat dissipation constraint information corresponding to each flight state, the stack temperature control information for each altitude condition is calculated using the stack temperature constraint information in the auxiliary component information.

[0015] The environmental data sets corresponding to each altitude range, the power constraint information corresponding to each flight state, the heat dissipation constraint information corresponding to each flight state, the airflow control information for each altitude condition, and the stack temperature control information for each altitude condition are used as the operating boundary information of the aviation fuel cell.

[0016] Optionally, identifying the extreme operating range and the normal operating range of the aviation fuel cell based on the operating condition boundary information includes:

[0017] Identify the battery operating condition type corresponding to each altitude range, the battery operating condition type corresponding to each altitude condition, and the battery operating condition type corresponding to each flight state; the battery operating condition type includes extreme operating condition type and normal operating condition type;

[0018] The environmental data set corresponding to the extreme operating condition type, the power constraint information corresponding to the extreme operating condition type, the heat dissipation constraint information corresponding to the extreme operating condition type, the stack temperature control information corresponding to the extreme operating condition type, and the air flow control information corresponding to the extreme operating condition type are taken as the extreme operating condition range of the aviation fuel cell.

[0019] The environmental data set corresponding to the conventional operating condition type, the power constraint information corresponding to the conventional operating condition type, the heat dissipation constraint information corresponding to the conventional operating condition type, the stack temperature control information corresponding to the conventional operating condition type, and the air flow control information corresponding to the conventional operating condition type are taken as the conventional operating condition range of the aviation fuel cell.

[0020] Optionally, the step of constructing the simulation operation strategy for the aviation fuel cell based on the extreme operating condition range and the normal operating condition range includes:

[0021] The division intervals, power constraint intervals, heat dissipation constraint intervals, hydrogen flow intervals, and stack temperature intervals for each of the aforementioned environmental types are obtained. Based on each of the aforementioned intervals, the operating ranges corresponding to each of the aforementioned battery operating conditions are split and combined to obtain the initial simulation operation strategy for each of the aforementioned battery operating conditions.

[0022] In response to the staff's strategy deduplication and screening operation, among the initial simulation operation strategies, the simulation operation strategies that conform to the staff's determination are selected as the simulation operation strategies for the aviation fuel cell.

[0023] Optionally, based on the low-dimensional fuel cell model and the auxiliary component model, an initial aviation fuel cell model is constructed, including:

[0024] Identify the operational constraint information of the low-dimensional fuel cell model in each module, and identify the auxiliary constraint information of each sub-model in the auxiliary component model;

[0025] Based on the aforementioned operational constraint information, the simulation operation mode between the modules of the low-dimensional fuel cell model is generated, and based on the auxiliary constraint information of each sub-model, the simulation operation mode between the sub-modules of the auxiliary component model is generated.

[0026] Identify the association information between each of the sub-models and each of the modules, and based on the association information, perform model splicing processing on the low-dimensional fuel cell model and the auxiliary component model to obtain a first aviation fuel cell model. Then, based on the simulation operation mode between each of the modules and the simulation operation mode between each of the sub-modules, adjust the first aviation fuel cell model to obtain the initial aviation fuel cell model of the aviation fuel cell.

[0027] Optionally, based on the simulation results, the parameter fitting process is performed on each model parameter in the initial aviation fuel cell model to obtain the aviation fuel cell model, including:

[0028] Based on the simulation results of each of the conventional operating conditions, the model structure parameters of the aviation fuel cell model are fitted, and based on the simulation results of each of the extreme operating conditions, the model empirical formula parameters of the aviation fuel cell model are fitted.

[0029] Based on the structural parameters of each model and the empirical formula parameters of each model, the current parameters of the aviation fuel cell model are adjusted to obtain the aviation fuel cell model.

[0030] Optionally, the step of filtering the target operating condition information based on the simulation results includes:

[0031] Based on the simulation results of each of the simulation operation strategies, the failure rate of the aviation fuel cell corresponding to each of the simulation operation strategies, the operating efficiency of the aviation fuel cell corresponding to each of the simulation operation strategies, and the lifespan of the aviation fuel cell corresponding to each of the simulation operation strategies are calculated.

[0032] Based on the failure rate of the aviation fuel cell corresponding to each of the simulated operation strategies, the operating efficiency of the aviation fuel cell corresponding to each of the simulated operation strategies, and the lifespan of the aviation fuel cell corresponding to each of the simulated operation strategies, the condition advantage of each simulated operation strategy in each battery operating condition type is calculated by using the safety weight, lifespan weight, and operating weight corresponding to each battery operating condition type.

[0033] Based on the operational advantage of each simulation operation strategy in each battery operating condition type, the simulation operation strategies corresponding to each battery operating condition type are selected from the simulation operation strategies and used as the target operating condition information for each battery operating condition type.

[0034] Optionally, after filtering the target operating condition information based on the simulation results, the process further includes:

[0035] Among the various simulation operation strategies, a target simulation operation strategy is randomly selected, and the operating conditions of the target simulation operation strategy are simulated using the aviation fuel cell model to obtain the model simulation operation results of the aviation fuel cell model.

[0036] Based on the model simulation results of the target simulation operation strategy and the simulation results of the target simulation operation strategy, the simulation deviation of the aviation fuel cell is identified;

[0037] When the simulation deviation exceeds a preset deviation threshold, the model parameters of the aviation fuel cell model are adjusted based on the battery parameters of the aviation fuel cell to obtain a new aviation fuel cell model. The new aviation fuel cell model replaces the original aviation fuel cell model. The process then returns to the step of simulating the operating conditions of the target simulation operation strategy through the aviation fuel cell model to obtain the model simulation operation results of the aviation fuel cell model, until the simulation deviation is less than the preset deviation threshold.

[0038] Replace the existing aviation fuel cell model with the new aviation fuel cell model obtained from the last iteration.

[0039] Optionally, determining the target battery control information of the aviation fuel cell based on the target operation results includes:

[0040] Identify the battery control information corresponding to each target operating result, and construct the battery operating condition distribution information of the aviation fuel cell based on the target operating results corresponding to each target operating condition;

[0041] Based on the battery operating condition distribution information, the distribution range corresponding to each operating state of the aviation fuel cell is identified, and the battery control information of each target operating result corresponding to each operating state is used as the sub-battery control information corresponding to each operating state.

[0042] The sub-battery control information corresponding to all operating states is used as the target battery control information for the aviation fuel cell.

[0043] Secondly, this application also provides an operational evaluation device for an aviation fuel cell. The device includes:

[0044] The acquisition module is used to acquire flight environment information, flight power demand information, and auxiliary component information of the aviation fuel cell, and based on the flight environment information, the flight power demand information, and the auxiliary component information of the aviation fuel cell, identify the operating condition boundary information of the aviation fuel cell.

[0045] The first construction module is used to identify the extreme operating range and the normal operating range of the aviation fuel cell based on the operating condition boundary information, and to construct a simulation operation strategy for the aviation fuel cell based on the extreme operating range and the normal operating range.

[0046] The second construction module is used to obtain the simulation results obtained by the staff through the simulation operation based on each of the simulation operation strategies, the low-dimensional fuel cell model of the aviation fuel cell, and the auxiliary component model of the aviation fuel cell, and to construct the initial aviation fuel cell model of the aviation fuel cell based on the low-dimensional fuel cell model and the auxiliary component model.

[0047] The fitting module is used to perform parameter fitting processing on each model parameter in the initial aviation fuel cell model based on the simulation results, to obtain the aviation fuel cell model, and to determine each target operating condition information based on the simulation results.

[0048] The simulation module is used to simulate the control process of the aviation fuel cell under each of the target operating conditions based on the target operating condition information, through the aviation fuel cell model, to obtain the target operating results of the aviation fuel cell model, and to determine the target battery control information of the aviation fuel cell based on each of the target operating results.

[0049] Optionally, the acquisition module is specifically used for:

[0050] Based on the flight environment information, environmental data of different environment types are identified, and the environmental data of each environment type are divided and processed according to different altitude ranges to obtain environmental data groups corresponding to each altitude range;

[0051] Based on the flight power demand information, the power constraint information of the aviation fuel cell corresponding to different flight states and the heat dissipation constraint information corresponding to each flight state are identified. Based on the auxiliary component information of the aviation fuel cell, the airflow control information of the battery auxiliary components under different altitude conditions is identified.

[0052] Based on the power constraint information and heat dissipation constraint information corresponding to each flight state, the stack temperature control information for each altitude condition is calculated using the stack temperature constraint information in the auxiliary component information.

[0053] The environmental data sets corresponding to each altitude range, the power constraint information corresponding to each flight state, the heat dissipation constraint information corresponding to each flight state, the airflow control information for each altitude condition, and the stack temperature control information for each altitude condition are used as the operating boundary information of the aviation fuel cell.

[0054] Optionally, the first building module is specifically used for:

[0055] Identify the battery operating condition type corresponding to each altitude range, the battery operating condition type corresponding to each altitude condition, and the battery operating condition type corresponding to each flight state; the battery operating condition type includes extreme operating condition type and normal operating condition type;

[0056] The environmental data set corresponding to the extreme operating condition type, the power constraint information corresponding to the extreme operating condition type, the heat dissipation constraint information corresponding to the extreme operating condition type, the stack temperature control information corresponding to the extreme operating condition type, and the air flow control information corresponding to the extreme operating condition type are taken as the extreme operating condition range of the aviation fuel cell.

[0057] The environmental data set corresponding to the conventional operating condition type, the power constraint information corresponding to the conventional operating condition type, the heat dissipation constraint information corresponding to the conventional operating condition type, the stack temperature control information corresponding to the conventional operating condition type, and the air flow control information corresponding to the conventional operating condition type are taken as the conventional operating condition range of the aviation fuel cell.

[0058] Optionally, the first building module is specifically used for:

[0059] The division intervals, power constraint intervals, heat dissipation constraint intervals, hydrogen flow intervals, and stack temperature intervals for each of the aforementioned environmental types are obtained. Based on each of the aforementioned intervals, the operating ranges corresponding to each of the aforementioned battery operating conditions are split and combined to obtain the initial simulation operation strategy for each of the aforementioned battery operating conditions.

[0060] In response to the staff's strategy deduplication and screening operation, among the initial simulation operation strategies, the simulation operation strategies that conform to the staff's determination are selected as the simulation operation strategies for the aviation fuel cell.

[0061] Optionally, the second building module is specifically used for:

[0062] Identify the operational constraint information of the low-dimensional fuel cell model in each module, and identify the auxiliary constraint information of each sub-model in the auxiliary component model;

[0063] Based on the aforementioned operational constraint information, the simulation operation mode between the modules of the low-dimensional fuel cell model is generated, and based on the auxiliary constraint information of each sub-model, the simulation operation mode between the sub-modules of the auxiliary component model is generated.

[0064] Identify the association information between each of the sub-models and each of the modules, and based on the association information, perform model splicing processing on the low-dimensional fuel cell model and the auxiliary component model to obtain a first aviation fuel cell model. Then, based on the simulation operation mode between each of the modules and the simulation operation mode between each of the sub-modules, adjust the first aviation fuel cell model to obtain the initial aviation fuel cell model of the aviation fuel cell.

[0065] Optionally, the fitting module is specifically used for:

[0066] Based on the simulation results of each of the conventional operating conditions, the model structure parameters of the aviation fuel cell model are fitted, and based on the simulation results of each of the extreme operating conditions, the model empirical formula parameters of the aviation fuel cell model are fitted.

[0067] Based on the structural parameters of each model and the empirical formula parameters of each model, the current parameters of the aviation fuel cell model are adjusted to obtain the aviation fuel cell model.

[0068] Optionally, the fitting module is specifically used for:

[0069] Based on the simulation results of each of the simulation operation strategies, the failure rate of the aviation fuel cell corresponding to each of the simulation operation strategies, the operating efficiency of the aviation fuel cell corresponding to each of the simulation operation strategies, and the lifespan of the aviation fuel cell corresponding to each of the simulation operation strategies are calculated.

[0070] Based on the failure rate of the aviation fuel cell corresponding to each of the simulated operation strategies, the operating efficiency of the aviation fuel cell corresponding to each of the simulated operation strategies, and the lifespan of the aviation fuel cell corresponding to each of the simulated operation strategies, the condition advantage of each simulated operation strategy in each battery operating condition type is calculated by using the safety weight, lifespan weight, and operating weight corresponding to each battery operating condition type.

[0071] Based on the operational advantage of each simulation operation strategy in each battery operating condition type, the simulation operation strategies corresponding to each battery operating condition type are selected from the simulation operation strategies and used as the target operating condition information for each battery operating condition type.

[0072] Optionally, the device further includes:

[0073] The filtering module is used to randomly filter target simulation operation strategies from among the various simulation operation strategies, and simulate the operation conditions of the target simulation operation strategy through the aviation fuel cell model to obtain the model simulation operation results of the aviation fuel cell model.

[0074] The identification module is used to identify the simulation deviation of the aviation fuel cell based on the model simulation results of the target simulation operation strategy and the simulation results of the target simulation operation strategy.

[0075] The adjustment module is used to adjust the model parameters of the aviation fuel cell model based on the battery parameters of the aviation fuel cell when the simulation deviation is greater than a preset deviation threshold, to obtain a new aviation fuel cell model, and replace the aviation fuel cell model with the new aviation fuel cell model, and return to the step of simulating the operating conditions of the target simulation operation strategy through the aviation fuel cell model to obtain the model simulation operation results of the aviation fuel cell model, until the simulation deviation is less than the preset deviation threshold.

[0076] The replacement module is used to replace the aviation fuel cell model with the new aviation fuel cell model obtained in the last iteration.

[0077] Optionally, the simulation module is specifically used for:

[0078] Identify the battery control information corresponding to each target operating result, and construct the battery operating condition distribution information of the aviation fuel cell based on the target operating results corresponding to each target operating condition;

[0079] Based on the battery operating condition distribution information, the distribution range corresponding to each operating state of the aviation fuel cell is identified, and the battery control information of each target operating result corresponding to each operating state is used as the sub-battery control information corresponding to each operating state.

[0080] The sub-battery control information corresponding to all operating states is used as the target battery control information for the aviation fuel cell.

[0081] Thirdly, this application provides a computer device. The computer device includes a memory and a processor, the memory storing a computer program, and the processor executing the computer program to implement the steps of the method described in any one of the first aspects.

[0082] Fourthly, this application provides a computer-readable storage medium having a computer program stored thereon that, when executed by a processor, implements the steps of the method described in any one of the first aspects.

[0083] Fifthly, this application provides a computer program product. The computer program product includes a computer program that, when executed by a processor, implements the steps of the method described in any one of the first aspects.

[0084] The aforementioned operational evaluation method, apparatus, and computer equipment for aviation fuel cells acquire flight environment information, flight power demand information, and auxiliary component information of the aviation fuel cell. Based on these information, they identify the operating condition boundary information of the aviation fuel cell. Based on this boundary information, they identify the extreme operating condition range and the normal operating condition range of the aviation fuel cell. Based on these extreme and normal operating condition ranges, they construct a simulated operation strategy for the aviation fuel cell. Finally, they obtain the simulation results obtained by personnel conducting simulated operations using the aviation fuel cell based on each of the simulated operation strategies. A low-dimensional fuel cell model and an auxiliary component model for an aviation fuel cell are constructed. Based on the low-dimensional fuel cell model and the auxiliary component model, an initial aviation fuel cell model is built. Based on the simulation results, parameter fitting processing is performed on each model parameter in the initial aviation fuel cell model to obtain an aviation fuel cell model. Based on the simulation results, target operating condition information is selected. Based on the target operating condition information, the control process of the aviation fuel cell under the target operating condition information is simulated through the aviation fuel cell model to obtain the simulation results of the aviation fuel cell model. Based on the simulation results, the target battery control information of the aviation fuel cell is determined. This solution comprehensively considers the flight environment, power requirements, and accessory information of the aviation fuel cell to identify its operating condition boundaries, thereby obtaining the operating range corresponding to different operating condition types. This generates a simulated operating strategy for the aviation fuel cell. This approach not only comprehensively acquires all simulated operating strategies for different operating conditions but also improves the degree to which the simulated operating strategies consider the aviation environment. Then, using the low-dimensional fuel cell model and accessory models of this solution, an initial aviation fuel cell model is constructed. The simulation results of each simulated operating strategy are then used to fit the parameters of the initial aviation fuel cell model, resulting in the final aviation fuel cell model. Finally, this model is used to simulate the target operating conditions and analyze the target battery control information of the aviation fuel cell. This avoids the problem of not being able to directly obtain the actual control information of the aviation fuel cell, thus improving the accuracy of identifying fuel cell control strategies for variable environments. Attached Figure Description

[0085] Figure 1 This is a flowchart illustrating an operational evaluation method for an aviation fuel cell in one embodiment;

[0086] Figure 2 This is a table showing the operating conditions of a simulated operating strategy in one embodiment.

[0087] Figure 3 This provides constraint information for each model of an aviation fuel cell in one embodiment;

[0088] Figure 4 This is a schematic diagram of the process of fitting model parameters based on simulation results in one embodiment;

[0089] Figure 5 This is a schematic diagram illustrating the selection of target operating conditions in one embodiment;

[0090] Figure 6 This is a schematic diagram of battery operating condition distribution information in one embodiment;

[0091] Figure 7 This is a flowchart illustrating an example of operational evaluation of an aviation fuel cell in one embodiment;

[0092] Figure 8 This is a structural block diagram of an operational evaluation device for an aviation fuel cell in one embodiment;

[0093] Figure 9 This is an internal structural diagram of a computer device in one embodiment. Detailed Implementation

[0094] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0095] The operational evaluation method for aviation fuel cells provided in this application can be applied to application environments where control strategies for aviation fuel cells are acquired in variable environments. This method can be applied to a terminal, a server, or a system including both a terminal and a server, and is implemented through interaction between the terminal and the server. The terminal can be, but is not limited to, various personal computers, laptops, smartphones, tablets, etc. The terminal comprehensively considers the flight environment, power requirements, and accessory information of the aviation fuel cell to identify its operating boundary, thereby obtaining the operating range corresponding to different operating conditions. This generates a simulated operating strategy for the aviation fuel cell, comprehensively acquiring all simulated operating strategies for different operating conditions and improving the consideration of the aviation environment in the simulated operating strategies. Then, the low-dimensional fuel cell model and accessory model of this solution are used to construct an initial aviation fuel cell model. By simulating the operating results of each simulated operating strategy in the actual aviation fuel cell, the parameters of each model in the initial aviation fuel cell model are fitted to obtain the aviation fuel cell model. Finally, the aviation fuel cell model is used to simulate the target operating results under each target operating condition, and the target battery control information of the aviation fuel cell is analyzed. This avoids the problem that the actual control information of the aviation fuel cell cannot be directly obtained, thereby improving the identification accuracy of fuel cell control strategies for variable environments.

[0096] In one embodiment, such as Figure 1 As shown, an operational evaluation method for an aviation fuel cell is provided. Taking the application of this method to a terminal as an example, the method includes the following steps:

[0097] Step S101: Obtain flight environment information, flight power demand information, and auxiliary component information of the aviation fuel cell, and identify the operating boundary information of the aviation fuel cell based on the flight environment information, flight power demand information, and auxiliary component information of the aviation fuel cell.

[0098] In this embodiment, in response to the information upload operation by the staff, the terminal acquires flight environment information, flight power demand information, and auxiliary component information of the aircraft carrying the aviation fuel cell during flight. The flight environment information includes, but is not limited to, oxygen concentration information, temperature change information, humidity change information, and atmospheric pressure information. The flight power information includes the climb power demand information during the climb process and the cruise power demand information during the cruise process. The auxiliary component information refers to the auxiliary component characteristics of the aviation fuel cell's auxiliary devices. These auxiliary devices are used to control the air pressure, temperature, and other data input to the aviation fuel cell, and to perform functions such as heat dissipation. These auxiliary devices can be divided into an air supply subsystem and a heat dissipation subsystem based on different functions. The air supply subsystem supplies air to the aviation fuel cell, and the heat dissipation subsystem reduces the temperature of the aviation fuel cell, ensuring that its temperature remains within a specified range. Then, based on the flight environment information, flight power demand information, and auxiliary component information of the aviation fuel cell, the terminal identifies the operating boundary information of the aviation fuel cell. The operating boundary information is used to characterize the environmental data of the aviation fuel cell at different altitudes, the power constraints and heat dissipation constraints at different flight states, and the airflow control information and stack temperature control information at different altitudes. The specific identification process will be explained in detail later.

[0099] Step S102: Based on the operating condition boundary information, identify the extreme operating condition range and the normal operating condition range of the aviation fuel cell, and construct a simulation operation strategy for the aviation fuel cell based on the extreme operating condition range and the normal operating condition range.

[0100] In this embodiment, the terminal identifies the extreme operating condition range and the normal operating condition range of the aviation fuel cell based on the operating condition boundary information. Based on these ranges, a simulated operation strategy for the aviation fuel cell is constructed. The extreme operating condition range refers to the range of environmental data, power constraints, heat dissipation constraints, stack temperature control information, and airflow control corresponding to the extreme operating condition type of the battery. The normal operating condition range refers to the range of environmental data, power constraints, heat dissipation constraints, stack temperature control information, and airflow control corresponding to the normal operating condition type of the battery. Each simulated operation strategy consists of the operating input data for the aviation fuel cell under specific operating conditions, used to control the aviation fuel cell under those specific conditions, thereby identifying the operating results of the aviation fuel cell. The specific construction process will be explained in detail later.

[0101] Step S103: Obtain the simulation results obtained by the staff based on each simulation operation strategy, the low-dimensional fuel cell model of the aviation fuel cell, and the auxiliary component model of the aviation fuel cell. Based on the low-dimensional fuel cell model and the auxiliary component model, construct the initial aviation fuel cell model of the aviation fuel cell.

[0102] In this embodiment, the terminal acquires the simulation results obtained by the staff based on various simulation operation strategies, using the aviation fuel cell for simulation operation, the low-dimensional fuel cell model of the aviation fuel cell, and the auxiliary component model of the aviation fuel cell. Based on the low-dimensional fuel cell model and the auxiliary component model, an initial aviation fuel cell model is constructed. The low-dimensional fuel cell model and the auxiliary component model of the aviation fuel cell are physical structure models and do not include model operating parameters.

[0103] Step S104: Based on the simulation results, perform parameter fitting on each model parameter in the initial aviation fuel cell model to obtain the aviation fuel cell model, and determine the target operating condition information based on each simulation result.

[0104] In this embodiment, the terminal performs parameter fitting processing on each model parameter in the initial aviation fuel cell model based on the simulation results to obtain the aviation fuel cell model, and determines the target operating condition information based on the simulation results. The initial aviation fuel cell model and the aviation fuel cell model include not only the physical structure model of the aviation fuel cell, but also the operating logic of the aviation fuel cell and the parameters corresponding to the control logic.

[0105] Step S105: Based on the target operating condition information, the control process of the aviation fuel cell under the target operating condition information is simulated through the aviation fuel cell model to obtain the target operating results of the aviation fuel cell model, and the target battery control information of the aviation fuel cell is determined based on the target operating results.

[0106] In this embodiment, the terminal, based on the target operating condition information, simulates the control process of the aviation fuel cell under each target operating condition using an aviation fuel cell model, obtains the target operating results of the aviation fuel cell model, and determines the target battery control information of the aviation fuel cell based on the target operating results. The target battery control information includes the battery control strategy of the aviation fuel cell under different operating states. The specific determination process will be explained in detail later.

[0107] Based on the above scheme, by comprehensively considering the flight environment, flight power requirements, and accessory information of the aviation fuel cell, the operating boundary of the aviation fuel cell is identified, thereby obtaining the operating range corresponding to different operating conditions. This generates a simulation operation strategy for the aviation fuel cell, which not only comprehensively acquires all simulation operation strategies for different operating conditions but also improves the degree of consideration of the aviation environment in the simulation operation strategy. Then, the low-dimensional fuel cell model and accessory model of the aviation fuel cell in this scheme are used to construct an initial aviation fuel cell model. By simulating the operation results of each simulation operation strategy in the actual aviation fuel cell, the parameters of each model in the initial aviation fuel cell model are subjected to parameter fitting processing to obtain the aviation fuel cell model. Finally, the target operation results under each target operating condition information are simulated using the aviation fuel cell model, and the target battery control information of the aviation fuel cell is analyzed. This avoids the problem that the actual control information of the aviation fuel cell cannot be directly obtained, thereby improving the identification accuracy of fuel cell control strategies for variable environments.

[0108] Optionally, based on flight environment information, flight power demand information, and auxiliary component information of the aviation fuel cell, the operating boundary information of the aviation fuel cell is identified, including: based on flight environment information, identifying environmental data of different environment types, and dividing the environmental data of each environment type according to different altitude ranges to obtain environmental data groups corresponding to each altitude range; based on flight power demand information, identifying power constraint information and heat dissipation constraint information corresponding to different flight states of the aviation fuel cell, and based on auxiliary component information of the aviation fuel cell, identifying airflow control information of battery accessories under different altitude conditions; based on the power constraint information and heat dissipation constraint information corresponding to each flight state, calculating the stack temperature control information under each altitude condition through the stack temperature constraint information in the accessory information; and using the environmental data groups corresponding to each altitude range, the power constraint information, the heat dissipation constraint information, the airflow control information, and the stack temperature control information as the operating boundary information of the aviation fuel cell.

[0109] In this embodiment, the terminal identifies environmental data of different environmental types based on flight environment information, and divides the environmental data of each environmental type into different altitude ranges to obtain environmental data groups corresponding to each altitude range. These altitude ranges include, for example, the troposphere (0-11000 meters) and the lower stratosphere (11000-20000 meters).

[0110] Based on flight power demand information, the terminal identifies the power constraints and heat dissipation constraints of the aviation fuel cell under different flight states. Furthermore, based on the auxiliary component information of the aviation fuel cell, it identifies the airflow control information of the battery components under different altitude conditions. These flight states include climb flight and cruise flight.

[0111] Based on the power constraint information and heat dissipation constraint information corresponding to each flight state, the terminal calculates the stack temperature control information for each altitude condition using the stack temperature constraint information in the auxiliary component information. Finally, the terminal uses the environmental data sets corresponding to each altitude range, the power constraint information, the heat dissipation constraint information, the airflow control information, and the stack temperature control information for each altitude condition as the operating boundary information for the aviation fuel cell.

[0112] Specifically, modeling the operating environment of an aircraft can refer to the international standard atmospheric model, in which atmospheric temperature and pressure are set as piecewise functions of altitude, with the troposphere (0-11000 meters) as one segment and the lower stratosphere (11000-20000 meters) as another. Atmospheric density can be calculated using the ideal gas law, and the dynamic viscosity of the gas can be calculated using the Sutherland equation.

[0113] Aircraft power requirement analysis includes designing the operating current and voltage of the fuel cell stack. When designing an aviation fuel cell system, the weight distribution of the fuel cell, hydrogen storage system, and cooling system must be considered. When considering the operating voltage, the cooling system capacity can be used as a constraint: Assuming the rated cooling power is Q and the system's rated output power is W, then the fuel cell voltage efficiency should satisfy the following inequality: Based on this, the lower voltage limit can be calculated. Based on the power requirements, the corresponding upper limit of current can be calculated. Finally, many other factors need to be considered, such as battery temperature management, uniformity of current distribution, safety margin, etc. These factors will ultimately be quantitatively converted into loss factors and substituted into the polarization curve.

[0114] Considering the impact of fuel cell auxiliary components' operating characteristics on fuel cell operating conditions, including but not limited to the influence of the air supply system on current and the influence of the heat sink on stack operating temperature, under high-altitude conditions, the air compressor needs to provide sufficient air while maintaining the boost pressure level. Assuming the maximum air mass flow rate is q, then the system operating current... n is the number of electrons transferred per unit reaction, M is the relative molecular mass, and F is the Faraday constant. This represents the cathode excess coefficient. The heat dissipation capacity of the radiator is strongly correlated with the operating temperature of the fuel cell stack, i.e. On the other hand, excessively high or low stack temperatures have adverse effects on stack performance, namely... By combining the attenuation of voltage efficiency and the constraints of heat dissipation conditions, the reasonable temperature range of the fuel cell stack can be calculated.

[0115] Based on the above scheme, by identifying environmental data, constraint information, and control information under different altitude ranges, flight states, and altitude conditions, the operating boundary information of aviation fuel cells can be obtained, thereby improving the comprehensiveness and accuracy of the obtained operating boundary information of aviation fuel cells.

[0116] Optionally, based on the operating condition boundary information, the extreme operating condition range and the normal operating condition range of the aviation fuel cell are identified, including: identifying the battery operating condition type corresponding to each altitude range, the battery operating condition type corresponding to each altitude condition, and the battery operating condition type corresponding to each flight state; the battery operating condition type includes extreme operating condition type and normal operating condition type; the environmental data set corresponding to the extreme operating condition type, the power constraint information corresponding to the extreme operating condition type, the heat dissipation constraint information corresponding to the extreme operating condition type, the stack temperature control information corresponding to the extreme operating condition type, and the airflow control information corresponding to the extreme operating condition type are taken as the extreme operating condition range of the aviation fuel cell; the environmental data set corresponding to the normal operating condition type, the power constraint information corresponding to the normal operating condition type, the heat dissipation constraint information corresponding to the normal operating condition type, the stack temperature control information corresponding to the normal operating condition type, and the airflow control information corresponding to the normal operating condition type are taken as the normal operating condition range of the aviation fuel cell.

[0117] In this embodiment, the terminal identifies the battery operating condition type corresponding to each altitude range, each altitude condition, and each flight state. This battery operating condition type includes extreme operating condition types and normal operating condition types. Then, the terminal uses the environmental data set, power constraint information, heat dissipation constraint information, stack temperature control information, and airflow control information corresponding to the extreme operating condition type as the extreme operating condition operating range of the aviation fuel cell. Finally, the terminal uses the environmental data set, power constraint information, heat dissipation constraint information, stack temperature control information, and airflow control information corresponding to the normal operating condition type as the normal operating condition operating range of the aviation fuel cell.

[0118] Based on the above scheme, by splitting the operating condition boundary information into extreme operating condition ranges and normal operating condition ranges, the accuracy of classifying and analyzing different battery operating condition types is improved.

[0119] Optionally, based on the operating range under extreme and normal operating conditions, a simulation operation strategy for aviation fuel cells is constructed, including: obtaining the division intervals for each environmental type, each power constraint interval, each heat dissipation constraint interval, each hydrogen flow interval, and each stack temperature interval; and based on each interval, splitting and combining the operating range corresponding to each battery operating condition type to obtain the initial simulation operation strategy for each battery operating condition type; in response to the staff's strategy deduplication and screening operation, selecting the simulation operation strategy that conforms to the staff's determination from each initial simulation operation strategy as the simulation operation strategy for aviation fuel cells.

[0120] In this embodiment, the terminal acquires the intervals for each environmental type, power constraint intervals, heat dissipation constraint intervals, hydrogen flow intervals, and stack temperature intervals. Based on these intervals, the operating ranges corresponding to each battery operating condition type are split and combined to obtain the initial simulation operation strategy for each battery operating condition type. The intervals are determined by the staff based on different experimental requirements and the distinction between uncontrolled strategies for aviation fuel cells.

[0121] Then, in response to the staff's strategy deduplication and screening operation, the terminal selects the simulation operation strategy that matches the staff's determination from each initial simulation operation strategy, and uses it as the simulation operation strategy for the aviation fuel cell.

[0122] Each simulation strategy corresponds to a specific operating condition, and the corresponding operating condition table is as follows: Figure 2 As shown, the data includes environmental data of the gas fed into the fuel cell on the cathode and anode sides, as well as the operating conditions corresponding to different stack temperature sensitivities, cathode pressure sensitivities, cathode metering ratio sensitivities, and anode metering ratio sensitivities for the aero-fuel cell.

[0123] Based on the above scheme, by determining the simulation operation strategies of aviation fuel cells at preset intervals, the adjustability of determining the simulation operation strategies of aviation fuel cells, as well as the practicality and accuracy of analyzing control strategies for different experimental requirements and different aviation fuel cells are improved.

[0124] Optionally, based on the low-dimensional fuel cell model and the auxiliary component model, an initial aviation fuel cell model is constructed, including: identifying the operational constraint information of each module in the low-dimensional fuel cell model and identifying the auxiliary constraint information of each sub-model in the auxiliary component model; generating the simulation operation mode between each module of the low-dimensional fuel cell model based on the operational constraint information, and generating the simulation operation mode between each sub-module of the auxiliary component model based on the auxiliary constraint information of each sub-model; identifying the association information between each sub-model and each module; performing model splicing processing on the low-dimensional fuel cell model and the auxiliary component model based on the association information to obtain the first aviation fuel cell model; and adjusting the first aviation fuel cell model based on the simulation operation mode between each module and the simulation operation mode between each sub-module to obtain the initial aviation fuel cell model.

[0125] In this embodiment, the terminal identifies the operational constraint information of the low-dimensional fuel cell model in each module, and also identifies the auxiliary constraint information of each sub-model in the auxiliary component model. For example... Figure 3 As shown, the operational constraints include constraints for convective mass transfer processes, ideal open-circuit voltage, diffusion mass transfer processes, membrane suction and drainage processes, intramembrane water transfer, ohmic polarization loss, and overpotential of anode and cathode reactions. Auxiliary constraints include the pressure ratio, flow coefficient, power coefficient, adiabatic efficiency, specific velocity, and specific diameter for the air compressor model; heat transfer formulas, heat transfer temperature difference calculations, convective heat transfer calculations, and heat dissipation efficiency calculations for the radiator model; and flow formulas, pressure difference formulas, and pump work formulas for the hydrogen circulation pump model.

[0126] Then, based on the operational constraint information, the terminal generates the simulation operation mode between the modules of the low-dimensional fuel cell model, and based on the auxiliary constraint information of each sub-model, generates the simulation operation mode between the sub-modules of the auxiliary component model. Next, the terminal identifies the association information between each sub-model and each module, and based on this association information, performs model splicing processing on the low-dimensional fuel cell model and the auxiliary component model to obtain the first aviation fuel cell model. Then, based on the simulation operation mode between each module and the simulation operation mode between each sub-module, the first aviation fuel cell model is adjusted to obtain the initial aviation fuel cell model.

[0127] Based on the above scheme, an initial aviation fuel cell model is determined based on various constraint information and auxiliary constraint information, which improves the practicality and logic of the determined initial aviation fuel cell model.

[0128] Optionally, based on the simulation results, parameter fitting processing is performed on each model parameter in the initial aviation fuel cell model to obtain the aviation fuel cell model, including: fitting each model structural parameter of the aviation fuel cell model based on the simulation results of each normal operating condition type, and fitting each model empirical formula parameter of the aviation fuel cell model based on the simulation results of each extreme operating condition type; adjusting the current parameters of the aviation fuel cell model based on each model structural parameter and each model empirical formula parameter to obtain the aviation fuel cell model.

[0129] In this embodiment, the terminal fits the structural parameters of the aviation fuel cell model based on the simulation results of various conventional operating conditions, and fits the empirical formula parameters of the aviation fuel cell model based on the simulation results of various extreme operating conditions. Specifically, as shown... Figure 4 As shown, based on the simulation results of different conventional operating conditions, the terminal fits the stack structure parameters, internal resistance model adoption number, and electrochemical sub-model parameters of the aviation fuel cell model. Based on the simulation results of extreme operating conditions, the terminal fits the overpotential of the anode and cathode reactions and the water absorption curve of the proton exchange membrane of the aviation fuel cell model for calibration.

[0130] Finally, the terminal adjusts the current parameters of the aviation fuel cell model based on the structural parameters of each model and the empirical formula parameters of each model to obtain the aviation fuel cell model.

[0131] Based on the above scheme, by fitting the parameters of the aviation fuel cell model through various simulation results, the structural similarity, operational similarity, and control process similarity between the aviation fuel cell model and the actual aviation fuel cell are improved.

[0132] Optionally, based on the simulation results, information on each target operating condition is filtered, including: calculating the failure rate, operating efficiency, and lifespan of the aviation fuel cell corresponding to each simulation strategy based on the simulation results of each simulation strategy; calculating the operating condition advantage of each simulation strategy in each battery operating condition type based on the safety weight, lifespan weight, and operating weight corresponding to each battery operating condition type; and selecting each simulation strategy corresponding to each battery operating condition type as the target operating condition information for each battery operating condition type based on the operating condition advantage of each simulation strategy in each battery operating condition type.

[0133] In this embodiment, the terminal calculates the failure rate, operating efficiency, and lifespan of the corresponding aviation fuel cell based on the simulation results of each simulation operation strategy. Then, based on these parameters, the terminal calculates the operational advantage of each simulation operation strategy for each battery operating condition type, using safety weights, lifespan weights, and operating weights corresponding to different battery operating condition types. Finally, based on the operational advantage of each simulation operation strategy for each battery operating condition type, the terminal selects the simulation operation strategies corresponding to each battery operating condition type as target operating condition information for each battery operating condition type. Figure 5 As shown, target operating condition information is filtered from various simulation operation strategies based on three perspectives: operational safety, operational efficiency, and operational lifespan.

[0134] Specifically, from an operational safety perspective, safety risks can be quantified by a combination of failure rate (FR) and the severity of failure consequences (S). The optimization objective can be expressed as: Where FR: system failure rate, which can be obtained from historical data and failure modes; S: severity of failure consequences, based on the assessment of potential losses or impacts; k1, k2: weighting factors, adjusted according to specific circumstances. From the perspective of operational efficiency, energy conversion efficiency can be quantified by the ratio of the actual output power of the fuel cell to the theoretical maximum output power, and the objective function can be expressed as: ,in, This refers to the actual output power of the fuel cell system. This represents the theoretical output power calculated from the perspective of fuel consumption. Considering operational lifespan, the expected lifespan of a fuel cell system can be estimated using its performance degradation rate; therefore, the optimization objective can be expressed as: ,in, Let be the rate of performance degradation of the fuel cell over time. Furthermore, a weighted synthesis of multiple factors can be considered, which can be achieved through the weighted sum of multiple single objective functions:

[0135] ,in These are weighting factors corresponding to efficiency, safety, and lifespan, and can be adjusted according to actual conditions. Considering the large computational load and highly nonlinear mathematical relationships in the optimization problem, an artificial intelligence optimization algorithm is used for global optimization.

[0136] Based on the above scheme, by considering efficiency, safety, and lifespan, the target operating condition information is screened, which improves the rationality of the screened target operating condition information and enhances the realism of the target operating results obtained by the model simulating each target operating condition information.

[0137] Optionally, after filtering the target operating condition information based on the simulation results, the method further includes: randomly selecting a target simulation operating strategy from among the various simulation operating strategies, and simulating the operating conditions of the target simulation operating strategy using the aviation fuel cell model to obtain the model simulation results of the aviation fuel cell model; identifying the simulation deviation of the aviation fuel cell based on the model simulation results of the target simulation operating strategy; when the simulation deviation is greater than a preset deviation threshold, adjusting the model parameters of the aviation fuel cell model based on the battery parameters of the aviation fuel cell to obtain a new aviation fuel cell model, replacing the original aviation fuel cell model with the new aviation fuel cell model, and returning to the step of simulating the operating conditions of the target simulation operating strategy using the aviation fuel cell model to obtain the model simulation results of the aviation fuel cell model, until the simulation deviation is less than the preset deviation threshold, replacing the original aviation fuel cell model with the new aviation fuel cell model obtained in the last iteration.

[0138] In this embodiment, the terminal randomly selects a target simulation operation strategy from among various simulation operation strategies, and simulates the operating conditions of the target simulation operation strategy using an aviation fuel cell model to obtain the model simulation operation results of the aviation fuel cell model. Then, based on the model simulation operation results of the target simulation operation strategy and the simulation operation results of the target simulation operation strategy, the terminal identifies the simulation deviation degree of the aviation fuel cell.

[0139] When the simulation deviation exceeds a preset deviation threshold, the terminal adjusts the model parameters of the aviation fuel cell model based on the battery parameters of the aviation fuel cell to obtain a new aviation fuel cell model. The new aviation fuel cell model replaces the original aviation fuel cell model, and the process returns to the step of simulating the target simulation operation strategy through the aviation fuel cell model to obtain the model simulation operation results of the aviation fuel cell model. This process continues until the simulation deviation is less than the preset deviation threshold, at which point the new aviation fuel cell model obtained in the last iteration replaces the original aviation fuel cell model.

[0140] Based on the above scheme, the operating parameters of the aviation fuel cell model were adjusted by using the simulation results of aviation fuel cells, which improved the realism of aviation fuel cells in simulating various target operating conditions and reduced simulation deviations.

[0141] Optionally, based on the target operating results, the target battery control information for the aviation fuel cell is determined, including: identifying the battery control information corresponding to each target operating result, and constructing the battery operating condition distribution information of the aviation fuel cell based on the target operating results corresponding to each target operating condition; identifying the distribution range corresponding to each operating state of the aviation fuel cell based on the battery operating condition distribution information, and using the battery control information of each target operating result corresponding to each operating state as the sub-battery control information corresponding to each operating state; and using the sub-battery control information corresponding to all operating states as the target battery control information for the aviation fuel cell.

[0142] In this embodiment, the terminal identifies the battery control information corresponding to each target operating result and constructs the battery operating condition distribution information of the aviation fuel cell based on the target operating results corresponding to each target operating condition. The battery control information corresponding to each target operating result includes control information for the gas input to the aviation fuel cell, control information for the cathode and anode, control information for the sub-heating system, and control information for the stack reaction process, etc.

[0143] Then, based on the battery operating condition distribution information, the terminal identifies the distribution range corresponding to each operating state of the aviation fuel cell, and uses the battery control information of each target operating result corresponding to each operating state as the sub-battery control information for each operating state. For example... Figure 6 As shown, the battery operating condition distribution information can be divided according to the operating state into the normal operating zone corresponding to the normal operating state, surge constraint zone 1 and surge constraint zone 2 corresponding to the surge operating state, stack sealing constraint zone corresponding to the stack sealing operating state, motor performance constraint zone corresponding to the high-performance electrode operating state, maximum speed constraint zone corresponding to the maximum speed electrode operating state, and low efficiency zone corresponding to the low efficiency operating state.

[0144] The terminal uses the sub-battery control information corresponding to all operating states as the target battery control information for the aviation fuel cell.

[0145] Based on the above scheme, after obtaining the battery operating condition distribution information by distributing different target operating conditions, the target operating conditions corresponding to different working states are identified, thereby obtaining the sub-battery control information corresponding to each operating state, which improves the accuracy of battery control in different operating states.

[0146] This application also provides an example of operational evaluation for an aviation fuel cell, such as... Figure 7 As shown, the specific processing procedure includes the following steps:

[0147] Step S701: Obtain flight environment information, flight power requirement information, and auxiliary component information for aviation fuel cells.

[0148] Step S702: Based on flight environment information, identify environmental data of different environmental types, and divide the environmental data of each environmental type into different altitude ranges to obtain environmental data groups corresponding to each altitude range.

[0149] Step S703: Based on flight power demand information, identify the power constraint information of aviation fuel cells under different flight states and the heat dissipation constraint information under each flight state. Based on the auxiliary component information of aviation fuel cells, identify the airflow control information of battery auxiliary components under different altitude conditions.

[0150] Step S704: Based on the power constraint information and heat dissipation constraint information corresponding to each flight state, and through the fuel cell temperature constraint information in the auxiliary component information, calculate the fuel cell temperature control information for each altitude condition.

[0151] Step S705: The environmental data sets corresponding to each altitude range, the power constraint information corresponding to each flight state, the heat dissipation constraint information corresponding to each flight state, the airflow control information for each altitude condition, and the stack temperature control information for each altitude condition are used as the operating boundary information of the aviation fuel cell.

[0152] Step S706: Identify the battery operating condition type corresponding to each altitude range, the battery operating condition type corresponding to each altitude condition, and the battery operating condition type corresponding to each flight state; the battery operating condition type includes extreme operating condition type and normal operating condition type.

[0153] Step S707: The environmental data set corresponding to the extreme operating condition type, the power constraint information corresponding to the extreme operating condition type, the heat dissipation constraint information corresponding to the extreme operating condition type, the stack temperature control information corresponding to the extreme operating condition type, and the air flow control information corresponding to the extreme operating condition type are taken as the extreme operating condition range of the aviation fuel cell.

[0154] Step S708: The environmental data set corresponding to the normal operating condition type, the power constraint information corresponding to the normal operating condition type, the heat dissipation constraint information corresponding to the normal operating condition type, the stack temperature control information corresponding to the normal operating condition type, and the air flow control information corresponding to the normal operating condition type are taken as the normal operating condition range of the aviation fuel cell.

[0155] Step S709: Obtain the division intervals for each environmental type, each power constraint interval, each heat dissipation constraint interval, each hydrogen flow interval, and each stack temperature interval. Based on each interval, split and combine the operating ranges corresponding to each battery operating condition type to obtain the initial simulation operation strategy for each battery operating condition type.

[0156] Step S710: In response to the staff's strategy deduplication and screening operation, among each initial simulation operation strategy, the simulation operation strategy that matches the staff's determination is selected as the simulation operation strategy for the aviation fuel cell.

[0157] Step S711: Obtain the simulation results, low-dimensional fuel cell model, and auxiliary component model of the aviation fuel cell obtained by the staff through simulation operation based on various simulation operation strategies.

[0158] Step S712: Identify the operational constraint information of the low-dimensional fuel cell model in each module, and identify the auxiliary constraint information of each sub-model in the auxiliary model.

[0159] Step S713: Based on the operational constraint information, generate the simulation operation mode between the modules of the low-dimensional fuel cell model, and based on the auxiliary constraint information of each sub-model, generate the simulation operation mode between the sub-modules of the auxiliary model.

[0160] Step S714: Identify the association information between each sub-model and each module. Based on the association information, perform model splicing processing on the low-dimensional fuel cell model and the auxiliary component model to obtain the first aviation fuel cell model. Based on the simulation operation mode between each module and the simulation operation mode between each sub-module, adjust the first aviation fuel cell model to obtain the initial aviation fuel cell model.

[0161] Step S715: Based on the simulation results of various conventional operating conditions, fit the structural parameters of each model of the aviation fuel cell model, and based on the simulation results of various extreme operating conditions, fit the empirical formula parameters of each model of the aviation fuel cell model.

[0162] Step S716: Based on the structural parameters of each model and the empirical formula parameters of each model, adjust the current parameters of the aviation fuel cell model to obtain the aviation fuel cell model.

[0163] Step S717: Based on the simulation results of each simulation operation strategy, calculate the failure rate of the aviation fuel cell corresponding to each simulation operation strategy, the operating efficiency of the aviation fuel cell corresponding to each simulation operation strategy, and the lifespan of the aviation fuel cell corresponding to each simulation operation strategy.

[0164] Step S718: Based on the failure rate, operating efficiency, and lifespan of the aviation fuel cells corresponding to each simulation operation strategy, the operational advantage of each simulation operation strategy in each battery operating condition type is calculated by using the safety weight, lifespan weight, and operating weight corresponding to different battery operating condition types.

[0165] Step S719: Based on the operational advantage of each simulation operation strategy in each battery operating condition type, select each simulation operation strategy corresponding to each battery operating condition type from the simulation operation strategies and use it as the target operating condition information corresponding to each battery operating condition type.

[0166] Step S720: Randomly select a target simulation operation strategy from among the various simulation operation strategies, and simulate the operating conditions of the target simulation operation strategy using the aviation fuel cell model to obtain the model simulation operation results of the aviation fuel cell model.

[0167] Step S721: Based on the model simulation results of the target simulation operation strategy and the simulation results of the target simulation operation strategy, identify the simulation deviation of the aviation fuel cell.

[0168] Step S722: When the simulation deviation is greater than the preset deviation threshold, adjust the model parameters of the aviation fuel cell model based on the battery parameters of the aviation fuel cell to obtain a new aviation fuel cell model. Replace the aviation fuel cell model with the new aviation fuel cell model and return to the step of simulating the operating conditions of the target simulation operation strategy through the aviation fuel cell model to obtain the model simulation operation results of the aviation fuel cell model, until the simulation deviation is less than the preset deviation threshold.

[0169] Step S723: Replace the aviation fuel cell model with the new aviation fuel cell model obtained in the last iteration.

[0170] Step S724: Based on the target operating condition information, the control process of the aviation fuel cell under the target operating condition information is simulated through the aviation fuel cell model to obtain the target operating results of the aviation fuel cell model, and the target battery control information of the aviation fuel cell is determined based on the target operating results.

[0171] Step S725: Identify the battery control information corresponding to each target operating result, and construct the battery operating condition distribution information of the aviation fuel cell based on the target operating results corresponding to each target operating condition.

[0172] Step S726: Based on the battery operating condition distribution information, identify the distribution range corresponding to each operating state of the aviation fuel cell, and use the battery control information of each target operating result corresponding to each operating state as the sub-battery control information corresponding to each operating state.

[0173] Step S727: Use the sub-battery control information corresponding to all operating states as the target battery control information for the aviation fuel cell.

[0174] It should be understood that although the steps in the flowcharts of the embodiments described above are shown sequentially according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless explicitly stated herein, there is no strict order restriction on the execution of these steps, and they can be executed in other orders. Moreover, at least some steps in the flowcharts of the embodiments described above may include multiple steps or multiple stages. These steps or stages are not necessarily completed at the same time, but can be executed at different times. The execution order of these steps or stages is not necessarily sequential, but can be performed alternately or in turn with other steps or at least some of the steps or stages of other steps.

[0175] Based on the same inventive concept, this application also provides an aviation fuel cell operation evaluation device for implementing the above-described aviation fuel cell operation evaluation method. The solution provided by this device is similar to the solution described in the above method; therefore, the specific limitations of the one or more aviation fuel cell operation evaluation device embodiments provided below can be found in the limitations of the aviation fuel cell operation evaluation method described above, and will not be repeated here.

[0176] In one embodiment, such as Figure 8 As shown, an operational evaluation device for an aviation fuel cell is provided, comprising: an acquisition module 810, a first construction module 820, a second construction module 830, a fitting module 840, and a simulation module 850, wherein:

[0177] The acquisition module 810 is used to acquire flight environment information, flight power demand information, and auxiliary component information of the aviation fuel cell, and based on the flight environment information, the flight power demand information, and the auxiliary component information of the aviation fuel cell, identify the operating condition boundary information of the aviation fuel cell.

[0178] The first construction module 820 is used to identify the extreme operating range and the normal operating range of the aviation fuel cell based on the operating condition boundary information, and to construct a simulation operation strategy for the aviation fuel cell based on the extreme operating range and the normal operating range.

[0179] The second construction module 830 is used to obtain the simulation results obtained by the staff through the simulation operation based on each of the simulation operation strategies, the low-dimensional fuel cell model of the aviation fuel cell, and the auxiliary component model of the aviation fuel cell, and to construct the initial aviation fuel cell model of the aviation fuel cell based on the low-dimensional fuel cell model and the auxiliary component model.

[0180] The fitting module 840 is used to perform parameter fitting processing on each model parameter in the initial aviation fuel cell model based on the simulation results to obtain the aviation fuel cell model, and to determine each target operating condition information based on the simulation results.

[0181] The simulation module 850 is used to simulate the control process of the aviation fuel cell under each of the target operating conditions based on the target operating condition information, through the aviation fuel cell model, to obtain the target operating result of the aviation fuel cell model, and to determine the target battery control information of the aviation fuel cell based on each of the target operating results.

[0182] Optionally, the acquisition module 810 is specifically used for:

[0183] Based on the flight environment information, environmental data of different environment types are identified, and the environmental data of each environment type are divided and processed according to different altitude ranges to obtain environmental data groups corresponding to each altitude range;

[0184] Based on the flight power demand information, the power constraint information of the aviation fuel cell corresponding to different flight states and the heat dissipation constraint information corresponding to each flight state are identified. Based on the auxiliary component information of the aviation fuel cell, the airflow control information of the battery auxiliary components under different altitude conditions is identified.

[0185] Based on the power constraint information and heat dissipation constraint information corresponding to each flight state, the stack temperature control information for each altitude condition is calculated using the stack temperature constraint information in the auxiliary component information.

[0186] The environmental data sets corresponding to each altitude range, the power constraint information corresponding to each flight state, the heat dissipation constraint information corresponding to each flight state, the airflow control information for each altitude condition, and the stack temperature control information for each altitude condition are used as the operating boundary information of the aviation fuel cell.

[0187] Optionally, the first building module 820 is specifically used for:

[0188] Identify the battery operating condition type corresponding to each altitude range, the battery operating condition type corresponding to each altitude condition, and the battery operating condition type corresponding to each flight state; the battery operating condition type includes extreme operating condition type and normal operating condition type;

[0189] The environmental data set corresponding to the extreme operating condition type, the power constraint information corresponding to the extreme operating condition type, the heat dissipation constraint information corresponding to the extreme operating condition type, the stack temperature control information corresponding to the extreme operating condition type, and the air flow control information corresponding to the extreme operating condition type are taken as the extreme operating condition range of the aviation fuel cell.

[0190] The environmental data set corresponding to the conventional operating condition type, the power constraint information corresponding to the conventional operating condition type, the heat dissipation constraint information corresponding to the conventional operating condition type, the stack temperature control information corresponding to the conventional operating condition type, and the air flow control information corresponding to the conventional operating condition type are taken as the conventional operating condition range of the aviation fuel cell.

[0191] Optionally, the first building module 820 is specifically used for:

[0192] The division intervals, power constraint intervals, heat dissipation constraint intervals, hydrogen flow intervals, and stack temperature intervals for each of the aforementioned environmental types are obtained. Based on each of the aforementioned intervals, the operating ranges corresponding to each of the aforementioned battery operating conditions are split and combined to obtain the initial simulation operation strategy for each of the aforementioned battery operating conditions.

[0193] In response to the staff's strategy deduplication and screening operation, among the initial simulation operation strategies, the simulation operation strategies that conform to the staff's determination are selected as the simulation operation strategies for the aviation fuel cell.

[0194] Optionally, the second building module 830 is specifically used for:

[0195] Identify the operational constraint information of the low-dimensional fuel cell model in each module, and identify the auxiliary constraint information of each sub-model in the auxiliary component model;

[0196] Based on the aforementioned operational constraint information, the simulation operation mode between the modules of the low-dimensional fuel cell model is generated, and based on the auxiliary constraint information of each sub-model, the simulation operation mode between the sub-modules of the auxiliary component model is generated.

[0197] Identify the association information between each of the sub-models and each of the modules, and based on the association information, perform model splicing processing on the low-dimensional fuel cell model and the auxiliary component model to obtain a first aviation fuel cell model. Then, based on the simulation operation mode between each of the modules and the simulation operation mode between each of the sub-modules, adjust the first aviation fuel cell model to obtain the initial aviation fuel cell model of the aviation fuel cell.

[0198] Optionally, the fitting module 840 is specifically used for:

[0199] Based on the simulation results of each of the conventional operating conditions, the model structure parameters of the aviation fuel cell model are fitted, and based on the simulation results of each of the extreme operating conditions, the model empirical formula parameters of the aviation fuel cell model are fitted.

[0200] Based on the structural parameters of each model and the empirical formula parameters of each model, the current parameters of the aviation fuel cell model are adjusted to obtain the aviation fuel cell model.

[0201] Optionally, the fitting module 840 is specifically used for:

[0202] Based on the simulation results of each of the simulation operation strategies, the failure rate of the aviation fuel cell corresponding to each of the simulation operation strategies, the operating efficiency of the aviation fuel cell corresponding to each of the simulation operation strategies, and the lifespan of the aviation fuel cell corresponding to each of the simulation operation strategies are calculated.

[0203] Based on the failure rate of the aviation fuel cell corresponding to each of the simulated operation strategies, the operating efficiency of the aviation fuel cell corresponding to each of the simulated operation strategies, and the lifespan of the aviation fuel cell corresponding to each of the simulated operation strategies, the condition advantage of each simulated operation strategy in each battery operating condition type is calculated by using the safety weight, lifespan weight, and operating weight corresponding to each battery operating condition type.

[0204] Based on the operational advantage of each simulation operation strategy in each battery operating condition type, the simulation operation strategies corresponding to each battery operating condition type are selected from the simulation operation strategies and used as the target operating condition information for each battery operating condition type.

[0205] Optionally, the device further includes:

[0206] The filtering module is used to randomly filter target simulation operation strategies from among the various simulation operation strategies, and simulate the operation conditions of the target simulation operation strategy through the aviation fuel cell model to obtain the model simulation operation results of the aviation fuel cell model.

[0207] The identification module is used to identify the simulation deviation of the aviation fuel cell based on the model simulation results of the target simulation operation strategy and the simulation results of the target simulation operation strategy.

[0208] The adjustment module is used to adjust the model parameters of the aviation fuel cell model based on the battery parameters of the aviation fuel cell when the simulation deviation is greater than a preset deviation threshold, to obtain a new aviation fuel cell model, and replace the aviation fuel cell model with the new aviation fuel cell model, and return to the step of simulating the operating conditions of the target simulation operation strategy through the aviation fuel cell model to obtain the model simulation operation results of the aviation fuel cell model, until the simulation deviation is less than the preset deviation threshold.

[0209] The replacement module is used to replace the aviation fuel cell model with the new aviation fuel cell model obtained in the last iteration.

[0210] Optionally, the simulation module 850 is specifically used for:

[0211] Identify the battery control information corresponding to each target operating result, and construct the battery operating condition distribution information of the aviation fuel cell based on the target operating results corresponding to each target operating condition;

[0212] Based on the battery operating condition distribution information, the distribution range corresponding to each operating state of the aviation fuel cell is identified, and the battery control information of each target operating result corresponding to each operating state is used as the sub-battery control information corresponding to each operating state.

[0213] The sub-battery control information corresponding to all operating states is used as the target battery control information for the aviation fuel cell.

[0214] The modules in the aforementioned operational evaluation device for aviation fuel cells can be implemented entirely or partially through software, hardware, or a combination thereof. These modules can be embedded in or independent of the processor in a computer device, or stored in the memory of a computer device as software, so that the processor can call and execute the corresponding operations of each module.

[0215] In one embodiment, a computer device is provided, which may be a terminal, and its internal structure diagram may be as follows: Figure 9As shown, the computer device includes a processor, memory, communication interface, display screen, and input devices connected via a system bus. The processor provides computing and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage media. The communication interface is used for wired or wireless communication with external terminals; wireless communication can be achieved through Wi-Fi, mobile cellular networks, NFC (Near Field Communication), or other technologies. When the computer program is executed by the processor, it implements a method for evaluating the operation of an aviation fuel cell. The display screen can be an LCD screen or an e-ink screen. The input devices can be a touch layer covering the display screen, buttons, a trackball, or a touchpad on the computer device's casing, or an external keyboard, touchpad, or mouse.

[0216] Those skilled in the art will understand that Figure 9 The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the computer device to which the present application is applied. Specific computer devices may include more or fewer components than those shown in the figure, or combine certain components, or have different component arrangements.

[0217] In one embodiment, a computer device is provided, including a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to implement the steps of the method described in any one of the first aspects.

[0218] In one embodiment, a computer-readable storage medium is provided having a computer program stored thereon, which, when executed by a processor, implements the steps of the method described in any one of the first aspects.

[0219] In one embodiment, a computer program product is provided, including a computer program that, when executed by a processor, implements the steps of the method described in any one of the first aspects.

[0220] It should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, data stored, data displayed, etc.) involved in this application are all information and data authorized by the user or fully authorized by all parties.

[0221] Those skilled in the art will understand that all or part of the processes in the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium. When executed, the computer program can include the processes of the embodiments described above. Any references to memory, databases, or other media used in the embodiments provided in this application can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetic random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memory can include random access memory (RAM) or external cache memory, etc. By way of illustration and not limitation, RAM can take many forms, such as Static Random Access Memory (SRAM) or Dynamic Random Access Memory (DRAM). The databases involved in the embodiments provided in this application may include at least one type of relational database and non-relational database. Non-relational databases may include, but are not limited to, blockchain-based distributed databases. The processors involved in the embodiments provided in this application may be general-purpose processors, central processing units, graphics processing units, digital signal processors, programmable logic devices, quantum computing-based data processing logic devices, etc., and are not limited to these.

[0222] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0223] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of this patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this application should be determined by the appended claims.

Claims

1. A method for evaluating the operation of an aviation fuel cell, characterized in that, The method includes: The system acquires flight environment information, flight power demand information, and auxiliary component information of the aviation fuel cell, and identifies the operating boundary information of the aviation fuel cell based on the flight environment information, flight power demand information, and auxiliary component information of the aviation fuel cell. Based on the operating condition boundary information, the extreme operating condition range and the normal operating condition range of the aviation fuel cell are identified, and a simulation operation strategy for the aviation fuel cell is constructed based on the extreme operating condition range and the normal operating condition range. The simulation results obtained by the staff based on the simulation operation strategies are obtained through the simulation operation of the aviation fuel cell, the low-dimensional fuel cell model of the aviation fuel cell, and the auxiliary component model of the aviation fuel cell. Based on the low-dimensional fuel cell model and the auxiliary component model, the initial aviation fuel cell model of the aviation fuel cell is constructed. Based on the simulation results, parameter fitting processing is performed on each model parameter in the initial aviation fuel cell model to obtain the aviation fuel cell model, and based on each simulation result, the target operating condition information is determined. Based on the target operating condition information, the control process of the aviation fuel cell under the target operating condition information is simulated through the aviation fuel cell model to obtain the target operating result of the aviation fuel cell model. Based on the target operating result, the target battery control information of the aviation fuel cell is determined.

2. The method according to claim 1, characterized in that, The step of identifying the operating boundary information of the aviation fuel cell based on the flight environment information, the flight power demand information, and the auxiliary component information of the aviation fuel cell includes: Based on the flight environment information, environmental data of different environment types are identified, and the environmental data of each environment type are divided and processed according to different altitude ranges to obtain environmental data groups corresponding to each altitude range; Based on the flight power demand information, the power constraint information of the aviation fuel cell corresponding to different flight states and the heat dissipation constraint information corresponding to each flight state are identified. Based on the auxiliary component information of the aviation fuel cell, the airflow control information of the battery auxiliary components under different altitude conditions is identified. Based on the power constraint information and heat dissipation constraint information corresponding to each flight state, the stack temperature control information for each altitude condition is calculated using the stack temperature constraint information in the auxiliary component information. The environmental data sets corresponding to each altitude range, the power constraint information corresponding to each flight state, the heat dissipation constraint information corresponding to each flight state, the airflow control information for each altitude condition, and the stack temperature control information for each altitude condition are used as the operating boundary information of the aviation fuel cell.

3. The method according to claim 2, characterized in that, The step of identifying the extreme operating range and the normal operating range of the aviation fuel cell based on the operating condition boundary information includes: Identify the battery operating condition type corresponding to each altitude range, the battery operating condition type corresponding to each altitude condition, and the battery operating condition type corresponding to each flight state; the battery operating condition type includes extreme operating condition type and normal operating condition type; The environmental data set corresponding to the extreme operating condition type, the power constraint information corresponding to the extreme operating condition type, the heat dissipation constraint information corresponding to the extreme operating condition type, the stack temperature control information corresponding to the extreme operating condition type, and the air flow control information corresponding to the extreme operating condition type are taken as the extreme operating condition range of the aviation fuel cell. The environmental data set corresponding to the conventional operating condition type, the power constraint information corresponding to the conventional operating condition type, the heat dissipation constraint information corresponding to the conventional operating condition type, the stack temperature control information corresponding to the conventional operating condition type, and the air flow control information corresponding to the conventional operating condition type are taken as the conventional operating condition range of the aviation fuel cell.

4. The method according to claim 3, characterized in that, The simulation operation strategy for the aviation fuel cell, based on the extreme operating condition range and the normal operating condition range, includes: The division intervals, power constraint intervals, heat dissipation constraint intervals, hydrogen flow intervals, and stack temperature intervals for each of the aforementioned environmental types are obtained. Based on each of the aforementioned intervals, the operating ranges corresponding to each of the aforementioned battery operating conditions are split and combined to obtain the initial simulation operation strategy for each of the aforementioned battery operating conditions. In response to the staff's strategy deduplication and screening operation, among the initial simulation operation strategies, the simulation operation strategies that conform to the staff's determination are selected as the simulation operation strategies for the aviation fuel cell.

5. The method according to claim 1, characterized in that, Based on the low-dimensional fuel cell model and the auxiliary component model, an initial aviation fuel cell model is constructed, including: Identify the operational constraint information of the low-dimensional fuel cell model in each module, and identify the auxiliary constraint information of each sub-model in the auxiliary component model; Based on the aforementioned operational constraint information, the simulation operation mode between the modules of the low-dimensional fuel cell model is generated, and based on the auxiliary constraint information of each sub-model, the simulation operation mode between the sub-modules of the auxiliary component model is generated. Identify the association information between each of the sub-models and each of the modules, and based on the association information, perform model splicing processing on the low-dimensional fuel cell model and the auxiliary component model to obtain a first aviation fuel cell model. Then, based on the simulation operation mode between each of the modules and the simulation operation mode between each of the sub-modules, adjust the first aviation fuel cell model to obtain the initial aviation fuel cell model of the aviation fuel cell.

6. The method according to claim 4, characterized in that, Based on the simulation results, parameter fitting processing is performed on each model parameter in the initial aviation fuel cell model to obtain the aviation fuel cell model, including: Based on the simulation results of each of the conventional operating conditions, the model structure parameters of the aviation fuel cell model are fitted, and based on the simulation results of each of the extreme operating conditions, the model empirical formula parameters of the aviation fuel cell model are fitted. Based on the structural parameters of each model and the empirical formula parameters of each model, the current parameters of the aviation fuel cell model are adjusted to obtain the aviation fuel cell model.

7. The method according to claim 4, characterized in that, The determination of target operating condition information based on the simulation results includes: Based on the simulation results of each of the simulation operation strategies, the failure rate of the aviation fuel cell corresponding to each of the simulation operation strategies, the operating efficiency of the aviation fuel cell corresponding to each of the simulation operation strategies, and the lifespan of the aviation fuel cell corresponding to each of the simulation operation strategies are calculated. Based on the failure rate of the aviation fuel cell corresponding to each of the simulated operation strategies, the operating efficiency of the aviation fuel cell corresponding to each of the simulated operation strategies, and the lifespan of the aviation fuel cell corresponding to each of the simulated operation strategies, the condition advantage of each simulated operation strategy in each battery operating condition type is calculated by using the safety weight, lifespan weight, and operating weight corresponding to each battery operating condition type. Based on the operational advantage of each simulation operation strategy in each battery operating condition type, the simulation operation strategies corresponding to each battery operating condition type are selected from the simulation operation strategies and used as the target operating condition information for each battery operating condition type.

8. The method according to claim 7, characterized in that, After determining the target operating condition information based on the simulation results, the process further includes: Among the various simulation operation strategies, a target simulation operation strategy is randomly selected, and the operating conditions of the target simulation operation strategy are simulated using the aviation fuel cell model to obtain the model simulation operation results of the aviation fuel cell model. Based on the model simulation results of the target simulation operation strategy and the simulation results of the target simulation operation strategy, the simulation deviation of the aviation fuel cell is identified; When the simulation deviation exceeds a preset deviation threshold, the model parameters of the aviation fuel cell model are adjusted based on the battery parameters of the aviation fuel cell to obtain a new aviation fuel cell model. The new aviation fuel cell model replaces the original aviation fuel cell model. The process then returns to the step of simulating the operating conditions of the target simulation operation strategy through the aviation fuel cell model to obtain the model simulation operation results of the aviation fuel cell model, until the simulation deviation is less than the preset deviation threshold. Replace the existing aviation fuel cell model with the new aviation fuel cell model obtained from the last iteration.

9. The method according to claim 7, characterized in that, The determination of the target battery control information for the aviation fuel cell based on the target operation results includes: Identify the battery control information corresponding to each target operating result, and construct the battery operating condition distribution information of the aviation fuel cell based on the target operating results corresponding to each target operating condition; Based on the battery operating condition distribution information, the distribution range corresponding to each operating state of the aviation fuel cell is identified, and the battery control information of each target operating result corresponding to each operating state is used as the sub-battery control information corresponding to each operating state. The sub-battery control information corresponding to all operating states is used as the target battery control information for the aviation fuel cell.

10. An operational evaluation device for an aviation fuel cell, characterized in that, The device includes: The acquisition module is used to acquire flight environment information, flight power demand information, and auxiliary component information of the aviation fuel cell, and based on the flight environment information, the flight power demand information, and the auxiliary component information of the aviation fuel cell, identify the operating condition boundary information of the aviation fuel cell. The first construction module is used to identify the extreme operating range and the normal operating range of the aviation fuel cell based on the operating condition boundary information, and to construct a simulation operation strategy for the aviation fuel cell based on the extreme operating range and the normal operating range. The second construction module is used to obtain the simulation results obtained by the staff through the simulation operation based on each of the simulation operation strategies, the low-dimensional fuel cell model of the aviation fuel cell, and the auxiliary component model of the aviation fuel cell, and to construct the initial aviation fuel cell model of the aviation fuel cell based on the low-dimensional fuel cell model and the auxiliary component model. The fitting module is used to perform parameter fitting processing on each model parameter in the initial aviation fuel cell model based on the simulation results, to obtain the aviation fuel cell model, and to determine each target operating condition information based on the simulation results. The simulation module is used to simulate the control process of the aviation fuel cell under each of the target operating conditions based on the target operating condition information, through the aviation fuel cell model, to obtain the target operating results of the aviation fuel cell model, and to determine the target battery control information of the aviation fuel cell based on each of the target operating results.

11. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that, When the processor executes the computer program, it implements the steps of the method according to any one of claims 1 to 9.

12. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 9.

13. A computer program product, comprising a computer program, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 9.

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