Power distribution method and equipment of hydrogen fuel cell hybrid power aircraft and medium

Abstract

The invention discloses a power distribution method and equipment for a hydrogen fuel cell hybrid aircraft and a medium, and relates to the technical field of aircraft power. The method comprises the steps that after a kinetic model and an environment model of the aircraft are constructed, joint simulation is conducted to obtain the rotating speed requirement of each rotor wing under the set working condition, and then the power requirement of the aircraft under the set working condition is obtained; establishing a target function; establishing a fuel cell model and a lithium battery pack model, respectively inputting the power demand of the aircraft under the set working condition into the fuel cell model and the lithium battery pack model to obtain the fuel cell efficiency, the fuel cell temperature, the power fluctuation rate of the fuel cell, the lithium battery charge state and the lithium battery temperature, and adopting an annealing algorithm to carry out annealing on the lithium battery; and carrying out iterative solution on the target function based on the obtained data, and carrying out frequency domain decomposition on a power distribution scheme by adopting wavelet transform to obtain a final power distribution scheme. On the premise that the service life of the hydrogen fuel cell is guaranteed, the endurance time of the aircraft can be prolonged.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft power, and particularly to a power distribution method, device and medium for a hydrogen fuel cell hybrid aircraft. Background Art

[0002] In recent years, the application scope of aircraft has been continuously expanding. In the civilian field, it is widely used in industries such as agriculture, telemetry, disaster relief, logistics, and photography; in the military field, the advantages of long-term hovering and low cost of aircraft make it applied to tasks such as reconnaissance, attack, logistics, and information. With the expansion of the application field of aircraft, more and more requirements are put forward for aircraft. For traditional pure-electric aircraft, affected by the energy density of the battery pack, the endurance time is not high; for fuel-electric hybrid aircraft, its power system is too bulky, and the characteristics of the engine make it difficult to cope with complex high-altitude climate conditions, posing challenges to the control algorithm.

[0003] The hydrogen fuel cell hybrid system combines a hydrogen fuel cell and a lithium battery pack through a DC-DC converter, which while ensuring endurance, reduces the complexity and overall weight of the power system, and effectively reduces environmental pollution. However, the power characteristics of hydrogen fuel cells are different from those of fuel engines, and are greatly affected by external environmental temperature and air pressure. The traditional hybrid system energy management algorithm cannot meet the requirements. Summary of the Invention

[0004] The purpose of the present application is to provide a power distribution method, device and medium for a hydrogen fuel cell hybrid aircraft, which can improve the endurance time of the aircraft on the premise of ensuring the life of the hydrogen fuel cell.

[0005] To achieve the above purpose, the present application provides the following solutions:

[0006] In the first aspect, the present application provides a power distribution method for a hydrogen fuel cell hybrid aircraft, including:

[0007] Construct a dynamic model and an environment model of the aircraft; the environment model includes: an outdoor wind field model and an outdoor temperature model;

[0008] Based on the environment model and the dynamic model, perform joint simulation to obtain the rotational speed requirements of each rotor under a set working condition;

[0009] Based on the rotational speed requirements of each rotor under the set working condition, obtain the power requirement of the aircraft under the set working condition;

[0010] Establish an objective function;

[0011] Build a fuel cell model and a lithium battery pack model, and input the power requirements of the aircraft under the set working conditions into the fuel cell model and the lithium battery pack model respectively to obtain the fuel cell efficiency, fuel cell temperature, power volatility of the fuel cell, state of charge of the lithium battery, and lithium battery temperature;

[0012] Use the annealing algorithm to iteratively solve the objective function based on the fuel cell efficiency, the fuel cell temperature, the power volatility of the fuel cell, the state of charge of the lithium battery, and the lithium battery temperature to obtain a power distribution plan;

[0013] Use wavelet transform to perform frequency domain decomposition on the power distribution plan to obtain the final power distribution plan.

[0014] Optionally, the outdoor wind field model is simulated using the Dryden turbulent wind model.

[0015] Optionally, obtaining the power requirement of the aircraft under the set working conditions based on the rotational speed requirements of each rotor under the set working conditions includes:

[0016] Query the motor map based on the rotational speed requirements of each rotor under the set working conditions and integrate to obtain the power requirement of the aircraft under the set working conditions.

[0017] Optionally, the objective function is expressed as:

[0018] f(ω) = k1η ICE + k2f SOC + k3f T + k4V + k5ΔP 2 ;

[0019] In the formula, f(ω) represents the objective function value, ω represents the solution, k i (i = 1, 2,..., 5) represents the weight, η ICE represents the fuel cell efficiency, f SOC represents the state of charge requirement of the lithium battery, f T represents the temperature requirements of the fuel cell and the lithium battery, V represents the power volatility of the fuel cell, and ΔP represents the difference between the required power and the actual output power.

[0020] Optionally, the temperature requirements f of the fuel cell and the lithium battery T are expressed as:

[0021]

[0022] In the formula, T min represents the lowest temperature, T ICE represents the fuel cell temperature, T max represents the highest temperature, T BATIndicates the temperature of the lithium battery.

[0023] Optionally, the power volatility V of the fuel cell is expressed as:

[0024]

[0025] In the formula, P k+1 represents the fuel cell power at the (k + 1)-th moment, P k represents the fuel cell power at the k-th moment, N represents the statistical window of the fuel cell power volatility, and t represents the time difference between the (k + 1)-th moment and the k-th moment.

[0026] Optionally, an annealing algorithm is adopted to iteratively solve the objective function based on the fuel cell efficiency, the fuel cell temperature, the power volatility of the fuel cell, the state of charge of the lithium battery, and the temperature of the lithium battery to obtain a power distribution scheme, including:

[0027] Set the annealing temperature, and use the set annealing temperature as the temperature requirement for the fuel cell and the lithium battery, randomly initialize a solution, and determine the first objective function value based on the annealing temperature and the initial solution;

[0028] Generate a new solution by perturbation, and determine the second objective function value based on the newly generated solution by perturbation and the annealing temperature;

[0029] Determine whether the difference between the second objective function value and the first objective function value is greater than 0;

[0030] When the difference is less than or equal to 0, use the new solution as the optimal solution;

[0031] When the difference is greater than 0, use the new solution as the optimal solution according to the Metropolis criterion;

[0032] Judge whether the iteration times are reached to obtain a first judgment result;

[0033] When the first judgment result is no, return to the step of generating a new solution by perturbation and determining the second objective function value based on the newly generated solution by perturbation and the annealing temperature;

[0034] When the first judgment result is yes, judge whether the optimal solution meets the termination condition to obtain a second judgment result;

[0035] When the second judgment result is no, lower the annealing temperature, reset the iteration times, and then return to the step of generating a new solution by perturbation and determining the second objective function value based on the newly generated solution by perturbation and the annealing temperature;

[0036] When the second judgment result is yes, return the optimal solution to obtain the power distribution scheme.

[0037] Optionally, the final power distribution scheme is expressed as:

[0038]

[0039] Wherein, P ICE represents the output power of the fuel cell, P L represents the low-frequency quantity, P' BAT represents the output power of the final lithium battery, P BAT represents the output power of the lithium battery, P H represents the high-frequency quantity.

[0040] In a second aspect, the present application provides a computer device, including: a memory, a processor, and a computer program stored on the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the power distribution method for the hydrogen fuel cell hybrid aircraft provided above.

[0041] In a third aspect, the present application provides a computer-readable storage medium, on which a computer program is stored, and when the computer program is executed by a processor, the steps of the power distribution method for the hydrogen fuel cell hybrid aircraft provided above are implemented.

[0042] According to the specific embodiments provided by the present application, the present application has the following technical effects:

[0043] The present application provides a power distribution method, device and medium for a hydrogen fuel cell hybrid aircraft. By establishing a dynamic model of the aircraft and an outdoor wind field model, joint simulation is carried out to obtain the power demand of the aircraft under common working conditions. Then, a fuel cell model considering the influence of external environmental temperature, self-heating and intake pressure under the wind field, and a lithium battery pack model considering external environmental temperature and self-heating are established. By inputting their respective required powers, parameters such as battery temperature, lithium battery SOC, and fuel cell efficiency are output. Then, an objective function considering parameters such as fuel cell efficiency, fuel cell power change rate, and lithium battery pack SOC is designed. Finally, power distribution is carried out through an annealing algorithm and a wavelet transform algorithm, so that the endurance time of the aircraft can be improved on the premise of ensuring the life of the hydrogen fuel cell. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings required in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0045] Figure 1Schematic flow chart of a power distribution method for a hydrogen fuel cell hybrid aircraft provided by an embodiment of the present application;

[0046] Figure 2 Schematic diagram of a simulation structure provided by an embodiment of the present application;

[0047] Figure 3 Schematic diagram of the structure of a computer device provided by an embodiment of the present application. Detailed implementation manners

[0048] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0049] To make the above objects, features, and advantages of the present application more obvious and understandable, the present application will be further described in detail below in conjunction with the drawings and specific implementation manners.

[0050] In an exemplary embodiment, the present application provides a power distribution method for a hydrogen fuel cell hybrid aircraft. This method is executed by a computer device, specifically, it can be executed alone by a computer device such as a terminal or a server, or jointly executed by a terminal and a server. In the embodiments of the present application, this method is described by taking it as an example applied to a server. As Figure 1 shown, this method includes:

[0051] Step 100: Construct a dynamic model and an environment model of the aircraft. The environment model includes: an outdoor wind field model and an outdoor temperature model. Among them, it is assumed that the outdoor is a constant temperature environment in a short time, and the outdoor wind field model is simulated using the Dryden turbulent wind model. The specific principle is:

[0052] Decompose the spectral function of the outdoor wind field model to generate a wind field shaping filter, and the white noise of the turbulent wind field can be simulated through this filter.

[0053] The outdoor temperature model is that the temperature decreases as the altitude increases.

[0054] Step 101: Based on the environment model and the dynamic model, perform joint simulation to obtain the rotational speed requirements of each rotor under the set working conditions.

[0055] Step 102: Based on the rotational speed requirements of each rotor under the set working conditions, obtain the power requirements of the aircraft under the set working conditions.

[0056] Step 103: Establish an objective function. The objective function is expressed as:

[0057] f(ω) = k1η ICE + k2f SOC + k3f T + k4V + k5ΔP 2 。

[0058] In the formula, f(ω) represents the objective function value. ω represents the solution. k i (i = 1, 2,..., 5) represents the weight, η ICE represents the fuel cell efficiency. f SOC represents the State of Charge (SOC) demand of the lithium battery, SOC min is the minimum State of Charge, SOC is the State of Charge value of the lithium battery, and the SOC of the lithium battery should be ensured not to be too low to ensure the minimum reserve energy for landing. f T represents the temperature demand of the fuel cell and the lithium battery. The temperature demands of the fuel cell and the lithium battery should be satisfied within a certain range. There is T min represents the lowest temperature, T ICE represents the fuel cell temperature, T max represents the highest temperature, T BAT represents the lithium battery temperature. V represents the power volatility of the fuel cell, P k+1 represents the fuel cell power at the (k + 1)th moment, P k represents the fuel cell power at the kth moment, N represents the statistical window of the fuel cell power volatility, t represents the time difference between the (k + 1)th moment and the kth moment. ΔP represents the difference between the demand power and the output power.

[0059] Step 104: Establish a fuel cell model and a lithium battery pack model, and input the power demand of the aircraft under the set working conditions into the fuel cell model and the lithium battery pack model respectively to obtain the fuel cell efficiency, the fuel cell temperature, the power volatility of the fuel cell, the State of Charge of the lithium battery, and the lithium battery temperature.

[0060] Step 105: Use the annealing algorithm to iteratively solve the objective function based on the fuel cell efficiency, the fuel cell temperature, the power volatility of the fuel cell, the State of Charge of the lithium battery, and the lithium battery temperature to obtain the power distribution scheme.

[0061] Step 106: Use wavelet transform to perform frequency domain decomposition on the power distribution scheme to obtain the final power distribution scheme.

[0062] In another exemplary embodiment of the present application, taking a quadrotor aircraft as an example, the specific manifestation form of the dynamic model established in step 100 is described. Among them, the dynamic model of the quadrotor aircraft is expressed as:

[0063]

[0064] In the formula, x, y, z are the spatial positions of the aircraft, θ, ψ are the attitude angles of the aircraft, U i (i = 1, 2, 3, 4) are control variables, m is the mass of the aircraft, is the derivative of *, is the derivative of, ρ is the air density, S x 、S z and S y are the effective areas of the fuselage, C Wx and C Wy 、C Wz are the wind resistance coefficients, u W and v W 、w W are the wind speeds, L is the length of the aircraft arm, I yy 、I zz and I xx are the moments of inertia of the aircraft, p, q and r are the angular velocities of the aircraft in the body coordinate system, Ω is the rotor speed, M wx 、M wy and M Wz are the spiral torques caused by wind resistance, u, ν and w are the linear velocities of the aircraft in the body coordinate system. U i has the following relationship with the rotational speeds Ω i of each rotor of the aircraft:

[0065]

[0066] In the formula, k is the rotor lift coefficient, k d is the rotor torque coefficient.

[0067] In another exemplary embodiment of the present application, taking the simulation structure shown in Figure 2 as an example, the process of step 101 of the present application is described. Among them, the simulation result is the rotational speed requirement of each rotor, and the set working condition is determined by the application scenario. Based on this, the power requirement P req of the aircraft under the set working condition is obtained by querying the motor map and integrating for each rotor's rotational speed requirement under the set working condition. The motor map is obtained from the product manual of the motor manufacturer.

[0068] In another exemplary embodiment of the present application, the implementation process of step 104 provided by the present application is described as:

[0069] (1) Model the electrochemical reaction of the fuel cell in Simulink to obtain a fuel cell model. The inputs of this model include the input pressures p H and p O of the hydrogen source and the oxygen source, the external environmental temperature T out , the output power P ICE of the fuel cell, and the outputs include the fuel cell efficiency η ICE , the fuel cell temperature T ICE , and the power volatility V of the fuel cell.

[0070] (2) Model the equivalent circuit model of the lithium battery pack in Simulink to obtain a lithium battery pack model. The input of this model is the output power P BAT of the lithium battery, and the outputs are the lithium battery SOC and the lithium battery temperature T BAT .

[0071] In another exemplary embodiment of the present application, perform preliminary allocation through the annealing algorithm, take [P ICE , P BAT as the solution space. Based on this, the implementation process of step 105 includes:

[0072] Step 1: Set the annealing temperature T, and use the set annealing temperature T as the temperature requirement of the fuel cell and the lithium battery. Randomly initialize the solution ω, and determine the first objective function value based on the annealing temperature and the initial solution, denoted as f1(ω).

[0073] Step 2: Perturb to generate a new solution ω′, and determine the second objective function value based on the newly generated solution by perturbation and the annealing temperature, denoted as f(ω′).

[0074] Step 3: Determine whether the difference between the second objective function value and the first objective function value is greater than 0. When the difference is less than or equal to 0, take the new solution as the optimal solution. When the difference is greater than 0, then take the new solution as the optimal solution according to the Metropolis criterion. Among them, the difference between the second objective function value and the first objective function value is denoted as Δf = f(ω′) - f1(ω).

[0075] Step 4: Judge whether the iteration times are reached to obtain a first judgment result. When the first judgment result is no, return to step 2. When the first judgment result is yes, judge whether the optimal solution satisfies the termination condition to obtain a second judgment result. When the second judgment result is no, reduce the annealing temperature, reset the iteration times, and then return to step 2. When the second judgment result is yes, return the optimal solution to obtain a power allocation scheme.

[0076] In another exemplary embodiment of the present application, after preliminary allocation using the annealing algorithm, a global optimal power allocation scheme is obtained. However, P in the current power allocation scheme ICE There may be a problem of excessive fluctuations, which makes it difficult for the fuel cell to follow the target in actual control, so it is necessary to perform a secondary distribution of the required power of the fuel cell. Based on this, in this embodiment, wavelet transform is used to calculate the power of P within a short slice time Δt. ICE Perform frequency domain decomposition to obtain the high frequency quantity P H With low frequency quantity P L , the final power allocation scheme is:

[0077]

[0078] Where P ICE represents the output power of the fuel cell, P′ BAT Indicates the final output power of the lithium battery, P BAT Indicates the output power of the lithium battery.

[0079] Based on the above description, the present application takes into account the impact of complex climatic conditions on the aircraft power system, enhances the adaptability of the aircraft, reduces the power change rate of the hydrogen fuel cell, and weakens the aging of the hydrogen fuel cell.

[0080] In an exemplary embodiment, a computer device is provided. The computer device may be a server or a terminal. The internal structure diagram thereof may be as follows: Figure 3 As shown. The computer device includes a processor, a memory, an input / output interface (Input / Output, referred to as I / O) and a communication interface. Among them, the processor, the memory and the input / output interface are connected through a system bus, and the communication interface is connected to the system bus through the input / output interface. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store power distribution data of a hydrogen fuel cell hybrid aircraft. The input / output interface of the computer device is used to exchange information between the processor and an external device. The communication interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, a power distribution method for a hydrogen fuel cell hybrid aircraft is implemented.

[0081] Those skilled in the art will understand that Figure 3The structure shown is only a block diagram of some structures related to the solution of this application, and does not constitute a limitation on the computer device to which the solution of this application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine some components, or have different component arrangements. In an exemplary embodiment, a computer device is provided, including a memory and a processor. A computer program is stored in the memory, and when the processor executes the computer program, the steps in the above method embodiments are implemented.

[0082] In an exemplary embodiment, a computer-readable storage medium is provided, storing a computer program, and when the computer program is executed by a processor, the steps in the above method embodiments are implemented.

[0083] In an exemplary embodiment, a computer program product is provided, including a computer program, and when the computer program is executed by a processor, the steps in the above method embodiments are implemented.

[0084] 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 for analysis, stored data, displayed data, etc.) involved in this application are all information and data authorized by the user or fully authorized by all parties, and the collection, use, and processing of relevant data need to comply with relevant regulations.

[0085] Those of ordinary skill in the art can understand that all or part of the processes in the methods of the above embodiments can be completed by instructing relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above methods. Among them, any reference to a memory, database, or other medium used in the embodiments provided in the present application can include at least one of non-volatile and volatile memories. Non-volatile memories 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), magnetoresistive random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memories can include random access memory (RAM) or external cache memory, etc. By way of illustration and not limitation, RAM can be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM), etc.

[0086] The databases involved in the embodiments provided in the present application can include at least one of relational databases and non-relational databases. Non-relational databases can include distributed databases based on blockchain, etc., without limitation. The processors involved in the embodiments provided in the present application can be general-purpose processors, central processors, graphics processors, digital signal processors, programmable logic devices, data processing logics based on quantum computing, etc., without limitation.

[0087] The technical features of the above embodiments can be combined arbitrarily. For the sake of concise description, 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, it should be considered as the scope described in this specification.

[0088] Specific examples are used in this article to elaborate on the principles and implementation manners of the present application. The description of the above embodiments is only used to help understand the method and its core idea of the present application; at the same time, for those of ordinary skill in the art, according to the idea of the present application, there will be changes in the specific implementation manners and application scopes. In summary, the content of this specification should not be construed as a limitation to the present application.

Claims

1. A power distribution method for a hydrogen fuel cell hybrid aircraft, characterized in that: The power distribution method of the hydrogen fuel cell hybrid aircraft comprises: Constructing a dynamic model and an environmental model of the aircraft; the environmental model includes: an outdoor wind field model and an outdoor temperature model; Based on the environmental model and the dynamic model, a joint simulation is performed to obtain the rotation speed requirements of each rotor under a set working condition; The power requirement of the aircraft under the set working condition is obtained based on the speed requirement of each rotor under the set working condition; Establish the objective function; Establish a fuel cell model and a lithium battery pack model, and input the power demand of the aircraft under the set working conditions into the fuel cell model and the lithium battery pack model respectively, to obtain the fuel cell efficiency, fuel cell temperature, fuel cell power fluctuation rate, lithium battery state of charge and lithium battery temperature; Adopting an annealing algorithm, the objective function is iteratively solved based on the fuel cell efficiency, the fuel cell temperature, the power fluctuation rate of the fuel cell, the lithium battery state of charge and the lithium battery temperature to obtain a power allocation scheme; The power allocation scheme is decomposed in the frequency domain by using wavelet transform to obtain a final power allocation scheme.

2. The power distribution method of a hydrogen fuel cell hybrid aircraft according to claim 1, characterized in that: The outdoor wind field model is simulated by using the Dryden turbulent wind model.

3. The power distribution method of a hydrogen fuel cell hybrid aircraft according to claim 1, characterized in that: Based on the speed requirements of each rotor under the set working condition, the power requirement of the aircraft under the set working condition is obtained, including: Based on the speed requirements of each rotor under the set working conditions, the motor map is queried and integrated to obtain the power requirements of the aircraft under the set working conditions.

4. The power distribution method of a hydrogen fuel cell hybrid aircraft according to claim 1, characterized in that: The objective function is expressed as: f(ω)=k1η ICE +k2f SOC +k3f T +k4V+k5ΔP 2 ; In the formula, f(ω) represents the objective function value, ω represents the solution, and k i (i=1,2,...,5) represents the weight, η ICE represents the fuel cell efficiency, f SOC Indicates the state of charge requirement of the lithium battery, f T represents the temperature requirement of the fuel cell and lithium battery, V represents the power fluctuation rate of the fuel cell, and ΔP represents the difference between the required power and the actual output power.

5. The power distribution method for a hydrogen fuel cell hybrid aircraft according to claim 4, characterized in that: Temperature requirements for fuel cells and lithium batteries T It is expressed as: Where, T min Indicates the minimum temperature, T ICE represents the fuel cell temperature, T max Indicates the maximum temperature, T BAT Indicates the lithium battery temperature.

6. The power distribution method for a hydrogen fuel cell hybrid aircraft according to claim 4, characterized in that: The power fluctuation rate V of the fuel cell is expressed as: Where P k+1 represents the fuel cell power at time k+1, P k represents the fuel cell power at time k, N represents the statistical window of the fuel cell power fluctuation rate, and t represents the time difference between time k+1 and time k.

7. The power distribution method of a hydrogen fuel cell hybrid aircraft according to claim 1, characterized in that: The objective function is iteratively solved based on the fuel cell efficiency, the fuel cell temperature, the power fluctuation rate of the fuel cell, the lithium battery state of charge and the lithium battery temperature by using an annealing algorithm to obtain a power allocation scheme, including: Setting an annealing temperature, and using the set annealing temperature as a temperature requirement of a fuel cell and a lithium battery, randomly initializing a solution, and determining a first objective function value based on the annealing temperature and the initial solution; Perturbing to generate a new solution, and determining a second objective function value based on the new solution generated by the perturbation and the annealing temperature; Determine whether the difference between the second objective function value and the first objective function value is greater than 0; When the difference is less than or equal to 0, the new solution is taken as the optimal solution; When the difference is greater than 0, the new solution is taken as the optimal solution according to the Metropolis criterion; Determine whether the number of iterations has been reached, and obtain a first determination result; When the first judgment result is no, returning to the step of generating a new solution by perturbation, and determining a second objective function value based on the new solution generated by the perturbation and the annealing temperature; When the first judgment result is yes, judging whether the optimal solution satisfies a termination condition, and obtaining a second judgment result; When the second judgment result is no, lowering the annealing temperature, resetting the number of iterations, returning to the step of generating a new solution by perturbation, and determining a second objective function value based on the new solution generated by the perturbation and the annealing temperature; When the second judgment result is yes, the optimal solution is returned to obtain the power allocation scheme.

8. The power distribution method for a hydrogen fuel cell hybrid aircraft according to claim 1, characterized in that: The final power allocation scheme is expressed as: Where P ICE Represents the output power of the fuel cell, P L Represents low frequency quantity, P′ BAT Indicates the final output power of the lithium battery, P BAT Indicates the output power of lithium battery, P H Indicates high frequency quantity.

9. A computer device comprising: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the power distribution method for a hydrogen fuel cell hybrid aircraft according to any one of claims 1 to 8.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the power distribution method for a hydrogen fuel cell hybrid aircraft according to any one of claims 1 to 8 is implemented.

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