Fuel cell system control method, device, storage medium, and electronic device

Abstract

This disclosure relates to the field of aircraft, and more particularly to a fuel cell system control method, apparatus, storage medium, and electronic device. The fuel cell system control method includes: acquiring flight parameters of the aircraft, including the aircraft's altitude; determining the target flight condition of the aircraft based on the flight parameters; calculating the stack power requirement of the fuel cell system under the target flight condition; and controlling the fuel cell system to provide power support to the aircraft based on the stack power requirement. Through this method, the aircraft fuel cell system can better adapt to the power demands under different flight conditions, providing stable and sufficient power support to the aircraft, thereby improving the performance stability and reliability of the aircraft.

Description

Technical Field

[0001] This disclosure relates to the field of aircraft, and in particular to a fuel cell system control method, apparatus, storage medium, and electronic device. Background Technology

[0002] With the rapid development and widespread application of aircraft technology, the performance stability and reliability of aircraft in various complex environments have become a key research focus. In these complex environments, the power supply system of aircraft faces enormous challenges. Traditional battery-powered methods often struggle to meet the continuous and stable power supply requirements of aircraft under these extreme conditions.

[0003] Fuel cells, as a highly efficient and environmentally friendly energy source, can continuously convert chemical energy into electrical energy. However, the performance of fuel cell systems is affected by their operating environment and conditions, thus impacting the aircraft's power supply. Summary of the Invention

[0004] The main objective of this disclosure is to provide a fuel cell system control method, apparatus, storage medium, and electronic device, aiming to solve the technical problem that the performance of fuel cell systems in the prior art is affected by the working environment and operating conditions, thereby affecting the power supply of aircraft.

[0005] To achieve the above objectives, this disclosure proposes a fuel cell system control method, comprising:

[0006] The flight parameters of the aircraft are obtained, including the flight altitude of the aircraft.

[0007] Based on the flight parameters, the target flight conditions of the aircraft are determined;

[0008] Calculate the fuel cell stack power requirement of the aircraft's fuel cell system under the target flight conditions;

[0009] Based on the power demand of the fuel cell stack, the fuel cell system is controlled to provide power support to the aircraft.

[0010] Optionally, calculating the fuel cell stack power requirement of the aircraft's fuel cell system under the target flight condition includes:

[0011] Calculate the air flow requirement of the air compressor of the fuel cell system under the target flight condition; based on the air flow requirement, determine the required power of the air compressor of the fuel cell system under the target flight condition.

[0012] Based on the required power of the air compressor, calculate the required power of the fuel cell stack under the target flight conditions.

[0013] Optionally, calculating the stack power requirement of the fuel cell system under the target flight condition based on the power requirement of the air compressor includes:

[0014] If the target flight condition is a climb condition, then the first stack power requirement of the fuel cell system under the climb condition is calculated according to the following formula:

[0015] P stack1 =P air1 +P aff

[0016] Among them, P stack1 For the power required by the first fuel cell stack, P air1 For the required power of the air compressor, P aff This refers to the power required by other auxiliary components of the fuel cell system;

[0017] If the target flight condition is a high-altitude level flight condition, then the power requirement of the second stack of the fuel cell system under the high-altitude level flight condition is calculated according to the following formula:

[0018] P stack2 =P air1 +P aff -ΔP

[0019] Among them, P stack2 The second stack power requirement is given by ΔP, where ΔP is the increase in stack power of the fuel cell system when the airflow increases; or

[0020] If the target flight condition is a landing condition, then the power requirement of the third stack of the fuel cell system under the landing condition is calculated according to the following formula:

[0021] P stack3 =P air1 +P aff

[0022] Among them, P stack3 This is the power required for the third fuel cell stack.

[0023] Optionally, calculating the stack power requirement of the fuel cell system under the target flight condition based on the power requirement of the air compressor includes:

[0024] Calculate the increase in stack power of the fuel cell system according to the formula:

[0025] ΔP=P2-P1

[0026] Wherein, P1 is the first required power of the fuel cell system without considering flight altitude, and P2 is the second required power of the fuel cell system considering altitude.

[0027] Optionally, determining the compressor power requirement of the fuel cell system under the target flight condition based on the airflow demand includes:

[0028] The required power of the air compressor is calculated using the following formula:

[0029] P air1 =Q1P a k3 / η

[0030] Among them, P air1 Q1 represents the required power of the air compressor, and P represents the required airflow rate. a η is the working pressure of the air compressor, k3 is a constant, and η is the energy conversion efficiency of the air compressor.

[0031] Optionally, calculating the air flow requirement of the air compressor in the fuel cell system under the target flight condition includes:

[0032] Determine the initial airflow requirement, which is the airflow requirement of the fuel cell system under the target flight condition without considering changes in oxygen concentration;

[0033] Obtain a first relationship of change, which is used to characterize the relationship between oxygen content and flight altitude.

[0034] Calculate the airflow demand based on the initial airflow demand and the first change relationship;

[0035] The airflow requirement is calculated using the following formula:

[0036]

[0037] Where Q1 is the airflow requirement, k2 is a constant, and H is the flight altitude corresponding to the target flight condition.

[0038] Optionally, determining the initial airflow requirement includes:

[0039] Obtain a first relationship between the air flow requirement of the fuel cell system and the air compressor speed of the air compressor;

[0040] Obtain the second relationship between the air compressor speed and the flight altitude;

[0041] Based on the first and second relationships, a third relationship between the airflow requirement of the fuel cell system and the flight altitude is determined.

[0042] Calculate the initial airflow requirement based on the third relational expression;

[0043] The initial airflow requirement is calculated according to the following formula:

[0044] Q0=k0k1H

[0045] Where Q0 is the initial airflow requirement, k0 and k1 are constants, and H is the flight altitude corresponding to the target flight condition.

[0046] Optionally, obtaining the first change relationship includes:

[0047] Collect oxygen content at different flight altitudes;

[0048] The first variation relationship is obtained by curve fitting of the different flight altitudes and the corresponding oxygen content at the different flight altitudes;

[0049] The first relationship of change can be expressed by the following exponential relationship:

[0050] O2=O′2*e -k H0

[0051] Where O2 is the oxygen content relative to sea level, O2′ is the oxygen content at sea level, k is a constant, and H0 is the flight altitude.

[0052] In addition, to achieve the above objectives, this disclosure also provides a fuel cell system control device, comprising:

[0053] An acquisition module is used to acquire the flight parameters of the aircraft, including the flight altitude of the aircraft.

[0054] The determination module is used to determine the target flight conditions of the aircraft based on the flight parameters.

[0055] The calculation module is used to calculate the stack power requirement of the fuel cell system of the aircraft under the target flight conditions;

[0056] The control module is used to control the fuel cell system to provide power support to the aircraft based on the power demand of the fuel cell stack.

[0057] In addition, to achieve the above objectives, this disclosure also provides a computer-readable storage medium storing a computer program, on which a processor executes the computer program to implement the above-described method.

[0058] In addition, to achieve the above objectives, this disclosure also provides an electronic device including a memory and a processor, wherein the memory stores a computer program and the processor executes the computer program to implement the above-described method.

[0059] In addition, to achieve the above objectives, this disclosure also provides a computer program product that implements the above-described method when run by a processor.

[0060] The fuel cell system control method, apparatus, storage medium, and electronic equipment disclosed in this disclosure first acquire the flight parameters of the aircraft during flight, then determine the target flight condition of the aircraft based on the flight parameters, then calculate the stack power requirement of the fuel cell system under the target flight condition, and finally control the fuel cell system to provide power support to the aircraft based on the stack power requirement. In this way, the current flight condition of the aircraft can be determined based on the real-time acquired flight parameters, and the stack power required by the fuel cell system under that condition can be predicted and calculated. Subsequently, the operating state of the fuel cell is adjusted according to the calculated stack power requirement to ensure stable and sufficient power support for the aircraft. Through this method, the aircraft fuel cell system can better adapt to the power demand under different flight conditions, especially under extreme conditions such as high altitudes and rapid ascent / descent, still providing stable and sufficient power support to the aircraft, thereby improving the performance stability and reliability of the aircraft and avoiding system power waste. Attached Figure Description

[0061] To more clearly illustrate the technical solutions in the embodiments of this disclosure or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0062] Figure 1 This is a schematic diagram of the device structure of the hardware operating environment involved in the embodiments of this disclosure;

[0063] Figure 2 This is a schematic diagram of a fuel cell system structure according to an embodiment of the present disclosure;

[0064] Figure 3 This is a schematic flowchart of a fuel cell system control method according to an embodiment of the present disclosure;

[0065] Figure 4This is a schematic diagram illustrating the variation of the required airflow of an air compressor with altitude according to an embodiment of the present disclosure.

[0066] Figure 5 This is a schematic diagram illustrating the change of oxygen content with altitude according to an embodiment of the present disclosure;

[0067] Figure 6 This is a schematic diagram illustrating the variation of air compressor power with altitude in an air compressor according to an embodiment of this disclosure.

[0068] Figure 7 This is a schematic diagram illustrating the variation of system power requirements under different flight conditions according to an embodiment of the present disclosure.

[0069] Figure 8 This is a schematic diagram illustrating the variation of fuel cell power with load and airflow in an embodiment of this disclosure.

[0070] Figure 9 This is a structural block diagram of a fuel cell system control device according to an embodiment of the present disclosure.

[0071] The realization of the purpose, functional features and advantages of this disclosure will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0072] The technical solutions of the embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this disclosure, and not all of them. Based on the embodiments of this disclosure, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this disclosure.

[0073] Reference Figure 1 , Figure 1 This is a schematic diagram of the device structure of the hardware operating environment involved in the embodiments of this disclosure.

[0074] Typically, the device includes: at least one processor 301, a memory 302, and a fuel cell system control program stored on the memory 302 and executable on the processor 301, the fuel cell system control program being configured to implement the steps of the fuel cell system control method as described above.

[0075] Processor 301 may include one or more processing cores, such as a quad-core processor or an octa-core processor. Processor 301 may be implemented using at least one hardware form selected from DSP (Digital Signal Processing), FPGA (Field-Programmable Gate Array), and PLA (Programmable Logic Array). Processor 301 may also include a main processor and a coprocessor. The main processor, also known as a CPU (Central Processing Unit), is used to process data in the wake-up state; the coprocessor is a low-power processor used to process data in the standby state. In some embodiments, processor 301 may integrate a GPU (Graphics Processing Unit), which is responsible for rendering and drawing the content to be displayed on the screen. Processor 301 may also include an AI (Artificial Intelligence) processor, which processes information related to the operation of the fuel cell system control method, enabling the fuel cell system control method model to learn autonomously and improve efficiency and accuracy.

[0076] The memory 302 may include one or more storage media, which may be non-transitory. The memory 302 may also include high-speed random access memory and non-volatile memory, such as one or more disk storage devices or flash memory devices. In some embodiments, the non-transitory storage media in the memory 302 are used to store at least one instruction, which is executed by the processor 301 to implement the fuel cell system control method provided in the method embodiments of this disclosure.

[0077] In some embodiments, the terminal may further include a communication interface 303 and at least one peripheral device. The processor 301, memory 302, and communication interface 303 can be connected via a bus or signal line. Each peripheral device can be connected to the communication interface 303 via a bus, signal line, or circuit board. Specifically, the peripheral device includes at least one of a radio frequency circuit 304, a display screen 305, and a power supply 306.

[0078] The communication interface 303 can be used to connect at least one I / O (Input / Output) related peripheral device to the processor 301 and the memory 302. In some embodiments, the processor 301, the memory 302, and the communication interface 303 are integrated on the same chip or circuit board; in some other embodiments, any one or two of the processor 301, the memory 302, and the communication interface 303 can be implemented on separate chips or circuit boards, which is not limited in this embodiment.

[0079] The radio frequency (RF) circuit 304 is used to receive and transmit RF (Radio Frequency) signals, also known as electromagnetic signals. The RF circuit 304 communicates with communication networks and other communication devices via electromagnetic signals. The RF circuit 304 converts electrical signals into electromagnetic signals for transmission, or converts received electromagnetic signals back into electrical signals. Optionally, the RF circuit 304 includes: an antenna system, an RF transceiver, one or more amplifiers, a tuner, an oscillator, a digital signal processor, a codec chipset, a user identity module card, etc. The RF circuit 304 can communicate with other terminals through at least one wireless communication protocol. This wireless communication protocol includes, but is not limited to: metropolitan area networks (MANs), various generations of mobile communication networks (2G, 3G, 4G, and 5G), wireless local area networks (WLANs), and / or WiFi (Wireless Fidelity) networks. In some embodiments, the RF circuit 304 may also include circuitry related to NFC (Near Field Communication), which is not limited in this disclosure.

[0080] Display screen 305 is used to display a UI (User Interface). This UI may include graphics, text, icons, videos, and any combination thereof. When display screen 305 is a touch display screen, it also has the ability to collect touch signals on or above its surface. These touch signals can be input as control signals to processor 301 for processing. In this case, display screen 305 can also be used to provide virtual buttons and / or a virtual keyboard, also known as soft buttons and / or a soft keyboard. In some embodiments, display screen 305 can be a single screen, the front panel of an electronic device; in other embodiments, display screen 305 can be at least two screens, respectively disposed on different surfaces of the electronic device or in a folded design; in still other embodiments, display screen 305 can be a flexible display screen, disposed on a curved or folded surface of the electronic device. Furthermore, display screen 305 can be configured as a non-rectangular, irregular shape, i.e., a non-rectangular screen. Display screen 305 can be made of materials such as LCD (Liquid Crystal Display) or OLED (Organic Light-Emitting Diode).

[0081] Power supply 306 is used to supply power to various components in an electronic device. Power supply 306 can be AC ​​power, DC power, a disposable battery, or a rechargeable battery. When power supply 306 includes a rechargeable battery, the rechargeable battery can support wired or wireless charging. The rechargeable battery can also be used to support fast charging technology. Those skilled in the art will understand that... Figure 1 The structure shown does not constitute a limitation on the device and may include more or fewer components than shown, or combine certain components, or have different component arrangements.

[0082] Furthermore, this disclosure also proposes a storage medium storing a fuel cell system control program, which, when executed by a processor, implements the steps of the fuel cell system control method described above. Therefore, further details will not be repeated here. Additionally, the beneficial effects of using the same method will also not be repeated. For technical details not disclosed in the storage medium embodiments of this disclosure, please refer to the description of the method embodiments of this disclosure. As an example, program instructions can be deployed to execute on a single device, or on multiple devices located at one location, or on multiple devices distributed across multiple locations and interconnected via a communication network.

[0083] 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 program can be stored in a storage medium, and when executed, it can include the processes of the embodiments of the above methods. The storage medium can be a magnetic disk, optical disk, read-only memory (ROM), or random access memory (RAM), etc.

[0084] In related technologies, the airflow requirements of automotive fuel cells are mainly adjusted according to load changes. However, when an aircraft's fuel cell system flies at different altitudes, it faces not only load changes but also variations in oxygen concentration. These variations directly affect the system's airflow requirements, thereby altering the required speed of the air compressor in the fuel cell system. Ignoring the influence of altitude may result in the fuel cell system being unable to provide sufficient power support for the aircraft.

[0085] Even with a constant load, an increase in airflow will slightly boost the output power of a fuel cell. Ignoring this phenomenon in actual system control could not only lead to wasted power but also reduce the overall efficiency of the system.

[0086] In view of this, this disclosure proposes a fuel cell system control method, device, storage medium, and electronic equipment for aircraft, which fully considers actual factors under different flight conditions, such as changes in oxygen concentration caused by altitude, and aims to ensure that the system supply can accurately match the power demand of the aircraft under various flight conditions.

[0087] Figure 2 This is a schematic diagram of a fuel cell system structure according to an embodiment of the present disclosure. Figure 2 As shown, the fuel cell system includes an electrical subsystem, a thermal management subsystem, a hydrogen subsystem, and an air subsystem. In the air subsystem, auxiliary components such as the air compressor are powered by the fuel cell stack. During changes in the aircraft's flight altitude, variations in the oxygen content of the air cause changes in the fuel cell's airflow demand, which in turn alters the power demand of the air compressor. Therefore, this disclosure focuses on the power matching problem between the fuel cell stack and the air compressor, proposing a fuel cell system control method applicable to applications such as... Figure 2 The fuel cell system shown.

[0088] Reference Figure 3 , Figure 3 This is a flowchart illustrating a fuel cell system control method according to an embodiment of the present disclosure, including the following steps:

[0089] Step S11: Obtain the flight parameters of the aircraft, including the flight altitude of the aircraft.

[0090] Step S12: Determine the target flight conditions of the aircraft based on the flight parameters.

[0091] Step S13: Calculate the stack power requirement of the aircraft's fuel cell system under the target flight conditions.

[0092] Step S14: Based on the power demand of the fuel cell stack, control the fuel cell system to provide power support for the aircraft.

[0093] For example, flight parameters may include flight altitude, as well as one or more of flight speed, throttle and joystick operations, and horizon display; this disclosure does not specifically limit these parameters. Correspondingly, the target flight condition of the aircraft can be determined based on changes in flight altitude, flight speed, throttle and joystick operations, and horizon display within a preset time period.

[0094] The criteria for determining each flight condition can be set and adjusted according to different aircraft and / or different flight environments and flight missions, and are not limited in this disclosure. The specific methods for determining the target flight condition of the aircraft will not be elaborated in this disclosure.

[0095] The above technical solution first acquires the aircraft's flight parameters during flight, then determines the target flight condition based on these parameters, calculates the fuel cell stack power requirement of the aircraft's fuel cell system under the target flight condition, and finally controls the fuel cell system to provide power support to the aircraft based on the stack power requirement. In this way, the current flight condition of the aircraft can be determined based on the real-time acquired flight parameters, thereby predicting and calculating the required stack power of the fuel cell system under that condition. Subsequently, the operating state of the fuel cell is adjusted according to the calculated stack power requirement to ensure stable and sufficient power support for the aircraft. Through this method, the aircraft's fuel cell system can better adapt to the power demands under different flight conditions, especially in extreme conditions such as high altitudes and rapid ascent / descent, still providing stable and sufficient power support to the aircraft, thus improving the aircraft's performance stability and reliability, and avoiding power waste.

[0096] In possible ways, the stack power requirement of the aircraft's fuel cell system under target flight conditions is calculated, including:

[0097] Calculate the airflow requirements of the air compressor in the fuel cell system under the target flight conditions;

[0098] Based on the airflow requirements, determine the compressor power requirement of the fuel cell system under the target flight conditions.

[0099] Based on the power demand of the air compressor, calculate the stack power demand of the fuel cell system under the target flight conditions.

[0100] For example, firstly, the operation of a fuel cell system depends on the amount of air needed to react with hydrogen to generate electricity. This airflow requirement is influenced by several key factors, including the fuel cell stack power, stack efficiency, and reaction stoichiometry. Given the specificity of flight conditions, these parameters can vary; therefore, accurately calculating the airflow requirement to match the specific flight conditions is crucial.

[0101] Secondly, to meet the airflow requirements of the fuel cell system, an air compressor is typically used. The power requirement of the air compressor is not fixed but varies dynamically based on the required airflow, the compressor's efficiency, and other relevant system parameters. Based on the previously calculated airflow requirements, the power required by the air compressor under specific flight conditions can be accurately estimated.

[0102] Finally, based on the power requirements of the air compressor under specific operating conditions, the required stack power of the fuel cell system to meet the target flight conditions can be further derived. This calculation process not only ensures the stable operation of the system but also provides a scientific basis for optimizing the performance of the fuel cell system.

[0103] Among possible methods, the airflow requirements of the fuel cell system's air compressor under the target flight conditions are calculated, including:

[0104] Determine the initial airflow requirement, which is the airflow requirement of the fuel cell system under the target flight conditions without considering changes in oxygen concentration.

[0105] Obtain the first relationship, which is used to characterize the relationship between oxygen content and flight altitude;

[0106] Calculate the airflow demand based on the initial airflow demand and the first change relationship;

[0107] Calculate the airflow requirement using the following formula:

[0108]

[0109] Where Q1 is the airflow requirement, k2 is a constant, and H is the flight altitude corresponding to the target flight condition.

[0110] For example, based on the initial airflow demand Q0 and the first variation relationship, the relationship between the airflow demand of the fuel cell system and altitude, considering changes in oxygen concentration, can be obtained. Then, based on this relationship, the calculation formula for calculating the airflow demand is determined, where Q is the airflow demand of the fuel cell system and H0 represents different flight altitudes.

[0111] Figure 4 This is a schematic diagram illustrating the variation of required airflow rate of an air compressor with altitude according to an embodiment of this disclosure. Based on the third relational formula and... Figure 4 It can be seen that, considering the change in oxygen concentration with altitude, the rate of increase in airflow demand is faster with increasing altitude. Since airflow is directly proportional to the compressor speed, the compressor speed needs to increase accordingly to match the larger airflow demand of the fuel cell stack.

[0112] Determine the initial airflow requirement in the possible ways, including:

[0113] Obtain the first relationship between the air flow requirement of the fuel cell system and the air compressor speed;

[0114] Obtain the second relationship between air compressor speed and flight altitude;

[0115] Based on the first and second relations, determine the third relation between the airflow requirement of the fuel cell system and the flight altitude.

[0116] Calculate the initial airflow requirement based on the third relation;

[0117] The initial airflow requirement is calculated using the following formula:

[0118] Q0=k0k1H

[0119] Where Q0 is the initial airflow requirement, k0 and k1 are constants, and H is the flight altitude corresponding to the target flight condition.

[0120] For example, the first relation can be expressed as Q0 = k0N0, the second relation can be expressed as N0 = k1H0, and based on the first and second relations, the third relation can be obtained as Q0 = k0k1H0, where N0 is the air compressor speed and H0 is the different flight altitudes.

[0121] Specifically, the constant values ​​k0 and k1 are related to the specifications of the air compressor used. Different specifications of air compressors will have different relationships between the rate of air compression and the compressor speed. Since higher speeds provide more power, the air compressor can compress air and output it more quickly. Therefore, generally speaking, the air flow rate of an air compressor is positively correlated with its speed; that is, as the speed increases, the air flow rate also increases. This disclosure does not specifically limit the constant values ​​k0 and k1 or their determination methods in the embodiments.

[0122] Among the possible ways to obtain the first change relation, including:

[0123] Collect oxygen content at different flight altitudes;

[0124] Curve fitting was performed on different flight altitudes and the corresponding oxygen content at different flight altitudes to obtain the first variation relationship;

[0125] The first relationship of change can be expressed by the following exponential relationship:

[0126] O2=O′2*e -k H0

[0127] Where O2 is the oxygen content relative to sea level, O2′ is the oxygen content at sea level, k is a constant, and H0 is the flight altitude.

[0128] For example, oxygen content at different flight altitudes can be collected, and curve fitting can be performed on the data at different flight altitudes and for each flight altitude. By fitting, the change in oxygen content with flight altitude can be approximated as an exponential relationship. Then, based on the exponential relationship and the initial airflow requirement, the airflow requirement of the air compressor of the fuel cell system under the target flight conditions can be calculated.

[0129] Figure 5 This is a schematic diagram illustrating the change in oxygen content with altitude according to an embodiment of this disclosure. Figure 5 As shown, compared to the relative oxygen content at sea level, the relative oxygen content gradually decreases with increasing altitude.

[0130] Specifically, in addition to changes in altitude, oxygen content may also vary slightly in different geographical locations. These variations can be caused by various factors; for example, in urban or industrial areas, the presence of air pollutants may cause a slight decrease in oxygen content. Therefore, based on the actual application scenario, the oxygen content at different altitudes corresponding to the aircraft can be measured, and a constant value k can be determined by fitting a curve. This disclosure does not specifically limit the constant value k or its determination method.

[0131] In possible ways, the compressor power requirement of the fuel cell system under the target flight conditions is determined based on the airflow demand, including:

[0132] Calculate the required power of the air compressor using the following formula:

[0133] P air1 =Q1P a k3 / η

[0134] Among them, P air1 Q1 represents the required power of the air compressor, and P represents the required airflow rate. a η is the working pressure of the air compressor, k3 is a constant, and η is the energy conversion efficiency of the air compressor.

[0135] For example, based on the initial airflow demand Q0, the initial air compressor power demand P, without considering changes in oxygen concentration, can be calculated using the following formula. air0 The calculation formula:

[0136] P air0 =Q0P a k3 / η

[0137] Substituting the initial airflow demand Q0 obtained from the above calculation, we get:

[0138] P air0 =k0k1k3P a H / η

[0139] Therefore, when considering changes in oxygen concentration, based on the air flow demand Q1, the initial air compressor power demand P can be calculated as described above. air0 From the calculation formula, we can obtain:

[0140]

[0141] If the power unit is kW, the air flow unit is N*m3 / min, and the pressure unit is bar, then k3 can be 101.325.

[0142] For example, Figure 6 This is a schematic diagram illustrating a variation of the air compressor power as a function of altitude, representing a different embodiment of the present disclosure. Figure 6 It can be seen that, after considering the change of oxygen concentration with altitude, the power required by the air compressor increases at a faster rate as the altitude increases.

[0143] In one possible manner, the stack power requirement of the fuel cell system under the target flight conditions is calculated based on the power requirement of the air compressor, including:

[0144] If the target flight condition is a climb condition, the power requirement of the first stack of the fuel cell system under the climb condition is calculated according to the following formula:

[0145] P stack1 =P air1 +P aff

[0146] Among them, P stack1 For the power required by the first fuel cell stack, P air1 For the required power of the air compressor, P aff This is for the power requirements of other auxiliary components in the fuel cell system;

[0147] If the target flight condition is high-altitude level flight, the power requirement of the second stack of the fuel cell system under high-altitude level flight conditions is calculated according to the following formula:

[0148] P stack2 =P air1 +P aff -ΔP

[0149] Among them, P stack2 The second stack power requirement is given by ΔP, where ΔP is the increase in stack power of the fuel cell system when the airflow increases; or

[0150] If the target flight condition is landing, the power requirement of the third stack of the fuel cell system under landing conditions is calculated according to the following formula:

[0151] P stack3 =P air1 +P aff

[0152] Among them, P stack3 This is the power required for the third fuel cell stack.

[0153] For example, based on the above method for calculating the required power P of the air compressor... air1 From the calculation formula, we can obtain:

[0154]

[0155] Figure 7 This is a schematic diagram illustrating the variation in system power requirements under different flight conditions according to an embodiment of this disclosure. Figure 7 As shown, the flight conditions of an aircraft can include low-altitude level flight, climb, high-altitude level flight, landing, and low-altitude level flight. When considering altitude, the power demand of the fuel cell system increases during climb, high-altitude level flight, and landing.

[0156] It is worth noting that after descending from a high altitude to a low altitude and then entering level flight again, i.e., when the aircraft is in a low-altitude level flight condition, the required power P of the fourth electric stack of the air compressor can be calculated using the following formula. stack4 :

[0157]

[0158] In one possible manner, the stack power requirement of the fuel cell system under the target flight conditions is calculated based on the power requirement of the air compressor, including:

[0159] Calculate the increase in stack power of the fuel cell system based on the formula:

[0160] ΔP=P2-P1

[0161] Where P1 is the first power requirement of the fuel cell system without considering flight altitude, and P2 is the second power requirement of the fuel cell system considering altitude.

[0162] It should be understood that if the oxygen concentration changes with altitude, the fuel cell stack requires a greater airflow when flying at high altitudes, and increasing the airflow of the fuel cell stack will result in a slight increase in the power of the fuel cell stack.

[0163] Figure 8 This is a schematic diagram illustrating the variation of fuel cell stack power with load and airflow according to an embodiment of this disclosure. Figure 8 As shown, this power boost can be calibrated as ΔP. ​​The value of ΔP can be measured in advance before the aircraft performs flight operations, and this disclosure does not limit this aspect.

[0164] Reference Figure 9 , Figure 9 This is a structural block diagram of a fuel cell system control device according to an embodiment of the present disclosure. Based on the same inventive concept as the foregoing embodiments, the device includes:

[0165] The acquisition module 10 is used to acquire the flight parameters of the aircraft, including the flight altitude of the aircraft.

[0166] The determining module 20 is used to determine the target flight condition of the aircraft based on the flight parameters;

[0167] Calculation module 30 is used to calculate the stack power requirement of the fuel cell system of the aircraft under the target flight conditions;

[0168] The control module 40 is used to control the fuel cell system to provide power support to the aircraft based on the power demand of the fuel cell stack.

[0169] Optionally, the computing module 30 is used for:

[0170] Calculate the air flow requirements of the air compressor in the fuel cell system under the target flight conditions;

[0171] Based on the airflow requirement, determine the compressor power requirement of the fuel cell system under the target flight conditions.

[0172] Based on the required power of the air compressor, calculate the required power of the fuel cell stack under the target flight conditions.

[0173] Optionally, the computing module 30 is used for:

[0174] If the target flight condition is a climb condition, then the first stack power requirement of the fuel cell system under the climb condition is calculated according to the following formula:

[0175] P stack1 =P air1 +P aff

[0176] Among them, P stack1 For the power required by the first fuel cell stack, P air1 For the required power of the air compressor, P aff This refers to the power required by other auxiliary components of the fuel cell system;

[0177] If the target flight condition is a high-altitude level flight condition, then the power requirement of the second stack of the fuel cell system under the high-altitude level flight condition is calculated according to the following formula:

[0178] P stack2 =P air1 +P aff -ΔP

[0179] Among them, P stack2 The second stack power requirement is given by ΔP, where ΔP is the increase in stack power of the fuel cell system when the airflow increases; or

[0180] If the target flight condition is a landing condition, then the power requirement of the third stack of the fuel cell system under the landing condition is calculated according to the following formula:

[0181] P stack3 =P air1 +P aff

[0182] Among them, P stack3 This is the power required for the third fuel cell stack.

[0183] Optionally, the computing module 30 is used for:

[0184] Calculate the increase in stack power of the fuel cell system according to the formula:

[0185] ΔP=P2-P1

[0186] Wherein, P1 is the first required power of the fuel cell system without considering flight altitude, and P2 is the second required power of the fuel cell system considering altitude.

[0187] Optionally, the computing module 30 is used for:

[0188] The required power of the air compressor is calculated using the following formula:

[0189] P air1 =Q1P a k3 / η

[0190] Among them, P air1 Q1 represents the required power of the air compressor, and P represents the required airflow rate. a η is the working pressure of the air compressor, k3 is a constant, and η is the energy conversion efficiency of the air compressor.

[0191] Optionally, the computing module 30 is used for:

[0192] Determine the initial airflow requirement, which is the airflow requirement of the fuel cell system under the target flight condition without considering changes in oxygen concentration;

[0193] Obtain a first relationship of change, which is used to characterize the relationship between oxygen content and flight altitude.

[0194] Calculate the airflow demand based on the initial airflow demand and the first change relationship;

[0195] The airflow requirement is calculated using the following formula:

[0196]

[0197] Where Q1 is the airflow requirement, k2 is a constant, and H is the flight altitude corresponding to the target flight condition.

[0198] Optionally, the computing module 30 is used for:

[0199] Obtain a first relationship between the air flow requirement of the fuel cell system and the air compressor speed of the air compressor;

[0200] Obtain the second relationship between the air compressor speed and the flight altitude;

[0201] Based on the first and second relationships, a third relationship between the airflow requirement of the fuel cell system and the flight altitude is determined.

[0202] Calculate the initial airflow requirement based on the third relational expression;

[0203] The initial airflow requirement is calculated according to the following formula:

[0204] Q0=k0k1H

[0205] Where Q0 is the initial airflow requirement, k0 and k1 are constants, and H is the flight altitude corresponding to the target flight condition.

[0206] Optionally, the computing module 30 is used for:

[0207] Collect oxygen content at different flight altitudes;

[0208] The first variation relationship is obtained by curve fitting of the different flight altitudes and the corresponding oxygen content at the different flight altitudes;

[0209] The first relationship of change can be expressed by the following exponential relationship:

[0210] O2=O′2*e -k H0

[0211] Where O2 is the oxygen content relative to sea level, O2′ is the oxygen content at sea level, k is a constant, and H0 is the flight altitude.

[0212] It should be noted that since the steps performed by the device in this embodiment are the same as those in the aforementioned method embodiments, the specific implementation methods and the technical effects that can be achieved can be referred to the aforementioned embodiments, and will not be repeated here.

[0213] Furthermore, in one embodiment, the present disclosure also provides an electronic device, the device including a processor, a memory, and a computer program stored in the memory, the computer program being executed by the processor to implement the steps of the methods in the foregoing embodiments.

[0214] Furthermore, in one embodiment, the present disclosure also provides a computer storage medium storing a computer program that, when executed by a processor, implements the steps of the methods described in the foregoing embodiments.

[0215] In some embodiments, the computer-readable storage medium may be a memory such as FRAM, ROM, PROM, EPROM, EEPROM, flash memory, magnetic surface memory, optical disk, or CD-ROM; or it may be a device including one or any combination of the above-mentioned memories. The computer may be a variety of computing devices, including smart terminals and servers.

[0216] In some embodiments, executable instructions may take the form of a program, software, software module, script, or code, written in any form of programming language (including compiled or interpreted languages, or declarative or procedural languages), and may be deployed in any form, including as a standalone program or as a module, component, subroutine, or other unit suitable for use in a computing environment.

[0217] As an example, executable instructions may, but do not necessarily, correspond to files in the file system. They may be stored as part of a file that holds other programs or data, for example, in one or more scripts in a Hyper Text Markup Language (HTML) document, in a single file dedicated to the program in question, or in multiple co-located files (e.g., a file that stores one or more modules, subroutines, or code sections).

[0218] As an example, executable instructions can be deployed to execute on a single computing device, or on multiple computing devices located in one location, or on multiple computing devices distributed across multiple locations and interconnected via a communication network.

[0219] It should be noted that, in this document, the terms "comprising," "may include," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or system that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or system. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or system that includes that element.

[0220] The sequence numbers of the embodiments disclosed above are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0221] Through the above description of the embodiments, those skilled in the art can clearly understand that the methods of the above embodiments can be implemented by means of software plus necessary general-purpose hardware platforms. Of course, they can also be implemented by hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of this disclosure, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product is stored in a storage medium (such as read-only memory / random access memory, magnetic disk, optical disk) and includes several instructions to cause a multimedia terminal device (which may be a mobile phone, computer, television receiver, or network device, etc.) to execute the methods described in the various embodiments of this disclosure.

[0222] The above description is merely an optional embodiment of this disclosure and does not limit the patent scope of this disclosure. Any equivalent structural transformations made using the contents of this specification and drawings under the inventive concept of this disclosure, or direct / indirect applications in other related technical fields, are included within the patent protection scope of this disclosure.

Claims

1. A control method for a fuel cell system, characterized in that, include: The flight parameters of the aircraft are obtained, including the flight altitude of the aircraft. Based on the flight parameters, the target flight conditions of the aircraft are determined; Calculate the fuel cell stack power requirement of the aircraft's fuel cell system under the target flight conditions; Based on the power demand of the fuel cell stack, the fuel cell system is controlled to provide power support to the aircraft. The calculation of the fuel cell system stack power requirement of the aircraft under the target flight conditions includes: Calculate the air flow requirements of the air compressor in the fuel cell system under the target flight conditions; Based on the airflow requirement, determine the compressor power requirement of the fuel cell system under the target flight conditions. Based on the required power of the air compressor, calculate the required power of the fuel cell stack of the fuel cell system under the target flight conditions; The calculation of the air flow requirement of the air compressor of the fuel cell system under the target flight condition includes: Determine the initial airflow requirement, which is the airflow requirement of the fuel cell system under the target flight condition without considering changes in oxygen concentration; Obtain a first relationship of change, which is used to characterize the relationship between oxygen content and flight altitude. Calculate the airflow demand based on the initial airflow demand and the first change relationship; The airflow requirement is calculated using the following formula: in, To meet airflow requirements, For the initial airflow requirement, It is a constant. H The altitude is the altitude corresponding to the target flight condition.

2. The method according to claim 1, characterized in that, The step of calculating the stack power requirement of the fuel cell system under the target flight condition based on the power requirement of the air compressor includes: If the target flight condition is a climb condition, then the first stack power requirement of the fuel cell system under the climb condition is calculated according to the following formula: in, For the power required by the first fuel cell stack, For the required power of the air compressor, This refers to the power required by other auxiliary components of the fuel cell system; If the target flight condition is a high-altitude level flight condition, then the power requirement of the second stack of the fuel cell system under the high-altitude level flight condition is calculated according to the following formula: in, For the power required by the second fuel cell stack, The increase in the stack power of the fuel cell system when the airflow increases; If the target flight condition is a landing condition, then the power requirement of the third stack of the fuel cell system under the landing condition is calculated according to the following formula: in, This is the power required for the third fuel cell stack.

3. The method according to claim 2, characterized in that, The step of calculating the stack power requirement of the fuel cell system under the target flight condition based on the power requirement of the air compressor includes: Calculate the increase in stack power of the fuel cell system according to the formula: in, P 1 represents the first power requirement of the fuel cell system, without considering flight altitude. P 2 represents the second power requirement of the fuel cell system when altitude is taken into account.

4. The method according to claim 1, characterized in that, Determining the required air compressor power of the fuel cell system under the target flight condition based on the airflow demand includes: The required power of the air compressor is calculated using the following formula: in, For the required power of the air compressor, To meet airflow requirements, This refers to the working pressure of the air compressor. It is a constant. This refers to the energy conversion efficiency of the air compressor.

5. The method according to claim 1, characterized in that, Determining the initial airflow requirement includes: Obtain a first relationship between the air flow requirement of the fuel cell system and the air compressor speed, expressed as Q0 = k0N0; obtain a second relationship between the air compressor speed and the flight altitude, expressed as N0 = k1H0; Where N0 is the air compressor speed and H0 is the different flight altitudes; Based on the first and second relationships, a third relationship between the airflow requirement of the fuel cell system and the flight altitude is determined. Calculate the initial airflow requirement based on the third relational expression; The third relation is: in, For the initial airflow requirement, , All are constants. H The altitude is the altitude corresponding to the target flight condition.

6. The method according to claim 1, characterized in that, The acquisition of the first change relationship includes: Collect oxygen content at different flight altitudes; The first variation relationship is obtained by curve fitting of the different flight altitudes and the corresponding oxygen content at the different flight altitudes; The first relationship of change is expressed by the following exponential relationship: in, This refers to the oxygen content relative to sea level. The oxygen content at sea level. k It is a constant. This refers to the flight altitude.

7. A fuel cell system control device, characterized in that, The method for implementing the fuel cell system control method according to any one of claims 1-6 includes: An acquisition module is used to acquire the flight parameters of the aircraft, including the flight altitude of the aircraft. The determination module is used to determine the target flight conditions of the aircraft based on the flight parameters; The calculation module is used to calculate the stack power requirement of the fuel cell system of the aircraft under the target flight conditions; the control module is used to control the fuel cell system to provide power support to the aircraft based on the stack power requirement.

8. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program, and the processor executes the computer program to implement the method as described in any one of claims 1-6.

9. An electronic device, characterized in that, The electronic device includes a memory and a processor, wherein the memory stores a computer program and the processor executes the computer program to implement the method as described in any one of claims 1-6.

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