Energy management control system and method for fuel cell electric aircraft

Abstract

The invention discloses an energy management control system and method for a fuel cell electric aircraft, and belongs to the technical field of fuel cells, the energy management control system comprises a fuel cell assembly, a first DC / DC converter, a lithium battery, a solar panel, a second DC / DC converter, an energy management controller and a touch display module, and the lithium battery is used for outputting a second power signal. Energy is distributed according to needs, for example, when the energy consumption of a flight task is high, the hybrid power mode is automatically switched, the energy supply flexibility is enhanced, the touch display module gives consideration to task demand input and energy state display, the operation convenience and the monitoring intuition are improved, finally, the energy utilization efficiency is greatly improved, and the endurance time of the aircraft is prolonged. And meanwhile, the stability and reliability of energy supply in different task scenes are guaranteed.

Description

TECHNICAL FIELD

[0001] The application discloses an energy management control system and method of a fuel cell electric aircraft, and belongs to the technical field of fuel cells. BACKGROUND

[0002] At present, the power sources of unmanned aerial vehicles are roughly divided into fuel cells, batteries, solar cells and super capacitors. The above power sources do not take into account both high energy density and high power density. The power problem of a single power source unmanned aerial vehicle is difficult to solve at present, so the research on a hybrid power system unmanned aerial vehicle is particularly important.

[0003] Lithium batteries are the main energy source of most unmanned aerial vehicles at present. The power density of lithium batteries is high, the response is fast, and the lithium batteries can provide instantaneous power demand for unmanned aerial vehicles. However, the lithium batteries have long charging time, limited endurance time and need to be frequently charged. The lithium batteries may not be able to provide sufficient energy under high load and different working conditions. Fuel cells have large energy density and are suitable for long-distance and high-load tasks. Hydrogen fuel cells can be quickly refueled with hydrogen. Compared with lithium batteries, the hydrogen fuel cells have shorter charging time. However, hydrogen leakage of the fuel cells may cause potential risks. Safety problems must be considered when the fuel cells are used. SUMMARY

[0004] The purpose of the application is to solve the problem of how to significantly improve the endurance time, performance and sustainability of unmanned aerial vehicles to meet the needs of different application fields, and to provide an energy management control system and method of a fuel cell electric aircraft.

[0005] The technical scheme of the application is as follows: According to a first aspect of an embodiment of the present application, an energy management control system of a fuel cell electric aircraft is provided, comprising: a fuel cell assembly, the fuel cell assembly being configured to output a first power signal; a first DC / DC converter, a first end of the first DC / DC converter being electrically connected to an output end of the fuel cell assembly, the first DC / DC converter being configured to perform energy management optimization on the first power signal output by the fuel cell assembly; a lithium battery, the lithium battery being configured to output a second power signal; a solar panel, the solar panel being configured to output a third power signal; a second DC / DC converter, a first end of the second DC / DC converter being electrically connected to an output end of the solar panel, the second DC / DC converter being configured to perform energy management optimization on the second power signal output by the solar panel; an energy management controller, the energy management controller being electrically connected to one end of the lithium battery, a second end of the first DC / DC converter, and a second end of the second DC / DC converter, respectively, the energy management controller being configured to acquire an energy state of the lithium battery, an energy state of the solar panel, an energy state of the fuel cell, and a task demand, determine a working mode based on the energy state of the lithium battery, the energy state of the solar panel, the energy state of the fuel cell, and the task demand, the working mode comprising at least: a lithium battery mode, a fuel cell mode, a solar mode, and a hybrid mode; and a touch display module, the touch display module being electrically connected to the energy management controller, the touch display module being configured to acquire task demand data, and further configured to display the energy state of the lithium battery, the energy state of the solar panel, and the energy state of the fuel cell.

[0006] Further, the fuel cell assembly comprises: a hydrogen storage bottle, the hydrogen storage bottle having a first output port; a solenoid valve, a first end of the solenoid valve being connected to the first output port, the solenoid valve being configured to control an exhaust amount of hydrogen gas discharged from the hydrogen storage bottle; a pressure reducing valve, a first end of the pressure reducing valve being connected to a second end of the solenoid valve; a fuel cell, a first end of the fuel cell being connected to a second end of the pressure reducing valve, a second end of the fuel cell being electrically connected to the first end of the first DC / DC converter, the fuel cell being configured to output the first power signal.

[0007] Further, the control system further comprises: a first sensor, the first sensor being arranged on a connection line between the fuel cell and the first DC / DC converter, the first sensor being configured to detect a first voltage and a first current output by the fuel cell.

[0008] Further, the control system further comprises: a second sensor, the second sensor being arranged on a connection line between the first DC / DC converter and the energy management controller, the second sensor being configured to detect a second voltage and a second current output by the first DC / DC converter.

[0009] Further, the fuel cell assembly further comprises a flow sensor, the flow sensor is arranged on the pipeline between the pressure reducing valve and the fuel cell, and the flow sensor is used for detecting the hydrogen flow entering the fuel cell.

[0010] Further, the control system further comprises a third sensor, the third sensor is arranged on the connecting line between the lithium battery and the energy management controller, and the third sensor is used for detecting the third voltage and the third current output by the lithium battery.

[0011] Further, the control system further comprises a fourth sensor, the fourth sensor is arranged on the connecting line between the solar panel and the second DC / DC converter, and the fourth sensor is used for detecting the fourth voltage and the fourth current output by the solar panel.

[0012] Further, the control system further comprises a fifth sensor, the fifth sensor is arranged on the connecting line between the second DC / DC converter and the energy management controller, and the fifth sensor is used for detecting the fifth voltage and the fifth current output by the second DC / DC converter.

[0013] According to the second aspect of the embodiment of the present application, an energy management control method of a fuel cell electric aircraft is provided, which is applied to the energy management control system of the fuel cell electric aircraft of the first aspect, and the method comprises the following steps: the energy management controller acquires the electric energy state of the lithium battery, the electric energy state of the solar panel, the electric energy state of the electric energy state and the task demand in response to the starting signal of the electric aircraft.

[0014] Further, the control method further comprises the following steps: the energy management controller acquires the first voltage and the first current output by the fuel cell, the second voltage and the second current output by the first DC / DC converter, the hydrogen flow entering the fuel cell, the third voltage and the third current output by the lithium battery, the fourth voltage and the fourth current output by the solar panel and the fifth voltage and the fifth current output by the second DC / DC converter; the energy management controller determines the electric energy state of the lithium battery, the electric energy state of the solar panel and the electric energy state of the fuel cell based on the first voltage and the first current output by the fuel cell, the second voltage and the second current output by the first DC / DC converter, the third voltage and the third current output by the lithium battery, the fourth voltage and the fourth current output by the solar panel and the fifth voltage and the fifth current output by the second DC / DC converter; the energy management controller determines the hydrogen consumption based on the hydrogen flow entering the fuel cell; the energy management controller determines the fuel cell output power based on the second voltage and the second current; and the energy management controller determines the hydrogen leakage state based on the hydrogen consumption and the fuel cell output power, wherein the hydrogen leakage state at least comprises the non-leakage state, the slight leakage state and the severe leakage state.

[0015] The present application has the following advantages: The application provides an energy management control system and method of a fuel cell electric aircraft, power signals of a fuel cell and a solar panel are optimized by a first DC / DC converter and a second DC / DC converter respectively, energy output quality is improved, an energy management controller intelligently selects a working mode based on multi-energy states and task requirements, energy is distributed on demand, when energy consumption is high during a flight task, the system is automatically switched to a hybrid power mode, energy supply flexibility is enhanced, a touch display module considers task requirement input and energy state display, operation convenience and monitoring intuitiveness are improved, energy utilization efficiency is greatly improved, aircraft endurance time is prolonged, and energy supply stability and reliability in different task scenarios are ensured.

[0016] It should be understood that the foregoing general description and the following detailed description are only exemplary and explanatory, and are not limiting to the application. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is a structural diagram of a first embodiment of an energy management control system of a fuel cell electric aircraft according to an exemplary embodiment. DETAILED DESCRIPTION

[0018] The technical solutions of the application will be described in detail below with reference to the drawings. Obviously, the described embodiments are only a part of the embodiments of the application, rather than all the embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the application.

[0019] In the description of the application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation to the application.

[0020] In the description of the application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integral connection; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, or the internal communication of two elements. For those skilled in the art, the specific meaning of the above terms in the application can be understood according to the specific circumstances.

[0021] Embodiment one: as Figure 1According to an exemplary embodiment, an energy management control system of a fuel cell electric aircraft is shown, comprising: a fuel cell assembly, the fuel cell assembly being configured to output a first power signal; a first DC / DC converter, a first end of the first DC / DC converter being electrically connected to an output end of the fuel cell assembly, the first DC / DC converter being configured to perform energy management optimization on the first power signal output by the fuel cell assembly; a lithium battery, the lithium battery being configured to output a second power signal; a solar panel, the solar panel being configured to output a third power signal; a second DC / DC converter, a first end of the second DC / DC converter being electrically connected to an output end of the solar panel, the second DC / DC converter being configured to perform energy management optimization on the second power signal output by the solar panel; an energy management controller, the energy management controller being electrically connected to one end of the lithium battery, a second end of the first DC / DC converter, and a second end of the second DC / DC converter, respectively, the energy management controller being configured to obtain an energy state of the lithium battery, an energy state of the solar panel, an energy state of the fuel cell, and a task demand, determine a working mode based on the energy state of the lithium battery, the energy state of the solar panel, the energy state of the fuel cell, and the task demand, the working mode including at least: a lithium battery mode, a fuel cell mode, a solar mode, and a hybrid mode; and a touch display module, the touch display module being electrically connected to the energy management controller, the touch display module being configured to obtain task demand data, and further configured to display the energy state of the lithium battery, the energy state of the solar panel, and the energy state of the fuel cell.

[0022] By using the technical solution of the embodiment, the first DC / DC converter and the second DC / DC converter respectively optimize the power signals of the fuel cell and the solar panel, improving the quality of energy output. The energy management controller intelligently selects the working mode based on the states of multiple energy sources and the task demand, realizing on-demand energy distribution, such as automatically switching to the hybrid mode when the energy consumption of the flight task is high, enhancing the flexibility of energy supply. The touch display module takes into account the input of the task demand and the display of the energy state, improving the convenience of operation and the intuitiveness of monitoring. Ultimately, the energy utilization efficiency is greatly improved, the endurance time of the aircraft is prolonged, and the stability and reliability of energy supply in different task scenarios are ensured.

[0023] Further, the fuel cell assembly comprises: a hydrogen storage bottle, the hydrogen storage bottle having a first output port; an electromagnetic valve, a first end of the electromagnetic valve being connected to the first output port, the electromagnetic valve being configured to control the exhaust amount of hydrogen gas discharged from the hydrogen storage bottle; a pressure reducing valve, a first end of the pressure reducing valve being connected to a second end of the electromagnetic valve; a fuel cell, a first end of the fuel cell being connected to a second end of the pressure reducing valve, a second end of the fuel cell being electrically connected to the first end of the first DC / DC converter, the fuel cell being configured to output the first power signal.

[0024] By applying this embodiment, the hydrogen storage bottle can provide sufficient hydrogen reserves for the fuel cell, laying an energy foundation for the continuous output of electric energy; the solenoid valve can accurately control the exhaust volume of hydrogen discharged from the hydrogen storage bottle, avoid excessive consumption or insufficient supply of hydrogen, and realize on-demand regulation of hydrogen; the pressure reducing valve can stabilize the pressure of the hydrogen delivered by the solenoid valve, ensure that the pressure of the hydrogen entering the fuel cell is within an appropriate working range, ensure the stability of the fuel cell operating environment, and thus enable it to stably output the first power supply signal. After the signal is optimized by the first DC / DC converter, it can provide high-quality electric energy for the aircraft. Overall, it not only improves the accuracy and stability of the energy supply of the fuel cell component, reduces hydrogen waste, but also ensures the reliability of subsequent electric energy output, providing strong energy support for the efficient and stable operation of the aircraft.

[0025] In an exemplary embodiment, the control system further includes: a first sensor, the first sensor being disposed on the connection line between the fuel cell and the first DC / DC converter, the first sensor being used to detect a first voltage and a first current output by the fuel cell. By detecting the first voltage and the first current on the connection line between the fuel cell and the first DC / DC converter in real time, the output state of the fuel cell can be accurately captured, providing a basis for key electrical energy parameters for the energy management controller, enabling it to more accurately judge the operating performance and electrical energy supply capacity of the fuel cell, thereby optimizing the energy management strategy. At the same time, this real-time monitoring function helps to promptly detect abnormalities in fuel cell output, facilitating rapid system response and adjustment measures to avoid the impact of unstable output on subsequent energy conversion and supply, effectively improving the safety and stability of the fuel cell assembly and the accuracy of the entire energy management system's regulation, and providing an important guarantee for reliable energy supply for aircraft.

[0026] In one exemplary embodiment, the control system further includes a second sensor disposed on the connection line between the first DC / DC converter and the energy management controller. The second sensor is configured to detect a second voltage and a second current output by the first DC / DC converter. By real-time monitoring of the second voltage and second current on the connection line between the first DC / DC converter and the energy management controller, the second sensor accurately captures the optimized power output state of the first DC / DC converter, providing the energy management controller with key parameters of the converted energy. This allows the energy management controller to more comprehensively understand the actual optimized energy supply capacity of the fuel cell assembly and, in turn, more accurately formulate energy allocation strategies. Furthermore, this monitoring function facilitates timely detection of conversion anomalies in the first DC / DC converter, facilitating rapid system adjustments to ensure stable power quality input to the energy management controller. This coordinated monitoring function, in conjunction with the first sensor, further enhances the controllability of the entire energy conversion and supply chain, strengthens the accuracy and reliability of the energy management system, and provides more comprehensive assurance for stable aircraft power supply.

[0027] Further, the fuel cell assembly further comprises: a flow sensor, the flow sensor is arranged on the pipeline between the pressure reducing valve and the fuel cell, and the flow sensor is used for detecting the hydrogen flow entering the fuel cell. By detecting the hydrogen flow entering the fuel cell in the pipeline between the pressure reducing valve and the fuel cell in real time, the actual supply amount of hydrogen can be accurately grasped, and key parameters are provided for system regulation and control; the flow data can be fed back to the control system to assist in optimizing the exhaust amount of the electromagnetic valve and the pressure regulation of the pressure reducing valve, to realize accurate matching of the hydrogen flow, ensure efficient operation of the fuel cell under suitable hydrogen supply conditions, and avoid hydrogen waste or low power generation efficiency due to excessive flow. At the same time, abnormal hydrogen flow can be found in time, and pipeline or pressure reducing equipment failure can be quickly checked, to ensure the safety and stability of the fuel cell work, and thus ensure the continuous and stable output of the first power signal, to provide strong support for efficient and reliable operation of the aircraft energy system.

[0028] In the embodiment, the control system further comprises: a third sensor, the third sensor is arranged on the connecting line between the lithium battery and the energy management controller, and the third sensor is used for detecting the third voltage and the third current output by the lithium battery. By detecting the third voltage and the third current on the connecting line between the lithium battery and the energy management controller in real time, the real-time output state and the power supply capacity of the lithium battery can be accurately captured, and key operating parameters of the lithium battery are provided for the energy management controller; this enables the controller to more accurately judge the remaining power, discharge efficiency and health status of the lithium battery, and thus more accurately meets the actual demand when formulating an energy distribution strategy. At the same time, the monitoring function can timely find the abnormal output of the lithium battery, so that the system can quickly take protective measures to avoid excessive discharge or failure of the lithium battery, prolong the service life of the lithium battery, form a comprehensive monitoring network of multiple energy states with other sensors, and further improve the accuracy and safety of the regulation and control of the entire energy management system, to provide a more perfect guarantee for the stable and reliable supply of aircraft energy.

[0029] In the embodiment, the control system further comprises a fourth sensor arranged on a connection line between the solar panel and the second DC / DC converter, the fourth sensor being configured to detect a fourth voltage and a fourth current output by the solar panel. By detecting the fourth voltage and the fourth current on the connection line between the solar panel and the second DC / DC converter in real time, the real-time output state of the solar panel can be accurately captured, and key parameters of solar energy supply can be provided for the energy management controller; this enables the controller to accurately determine the actual power generation capacity of the solar panel affected by the light condition, and then more reasonably determine whether to enable the solar mode or adjust the participation ratio of solar energy in the hybrid mode when formulating an energy strategy, thereby improving the utilization rate of solar energy. At the same time, this monitoring function can timely find the abnormal output of the solar panel, so as to facilitate the system to quickly respond to avoid affecting the subsequent optimization processing of the second DC / DC converter, and cooperates with the second sensor to form a complete state monitoring of the solar energy from output to conversion, further perfects the multi-energy monitoring network, and improves the accuracy and adaptability of the whole energy management system, thereby providing reliable protection for efficient use of clean energy by the aircraft.

[0030] Further, the control system further comprises a fifth sensor arranged on a connection line between the second DC / DC converter and the energy management controller, the fifth sensor being configured to detect a fifth voltage and a fifth current output by the second DC / DC converter. By detecting the fifth voltage and the fifth current on the connection line between the second DC / DC converter and the energy management controller in real time, the output state of the solar electric energy after optimization by the second DC / DC converter can be accurately captured, and key parameters of the solar energy after conversion can be provided for the energy management controller, so that the energy management controller can more comprehensively master the actual energy supply capacity of the solar energy after optimization, and then more accurately allocate solar resources when formulating an energy distribution strategy; at the same time, this monitoring function can timely find the conversion abnormality of the second DC / DC converter, such as the output voltage or current deviating from the standard range, so as to facilitate the system to quickly respond to adjustment to ensure the stability of the quality of the solar electric energy input to the energy management controller, and form a whole-process monitoring closed loop of the solar energy from the original output to the optimized conversion with the fourth sensor, further perfect the multi-energy state monitoring system, and improve the accuracy and reliability of the whole energy management system, thereby providing a more solid guarantee for efficient and stable use of solar clean energy by the aircraft.

[0031] Embodiment two: an energy management control method of a fuel cell electric aircraft according to an example embodiment, the method comprising the following steps: After the energy management controller is triggered by the start signal of the electric aircraft, the complete energy management process is started, and the specific steps are as follows: Firstly, in response to the start signal, the initial acquisition of the lithium battery power state, the solar panel power state, the fuel cell power state, the lithium battery power state at least includes: the remaining power and the discharge depth, etc., the solar panel power state at least includes: the current power generation and the output capacity affected by the light intensity, etc., the fuel cell power state at least includes: the current output power and the working temperature, etc., and at the same time, the user input task demand is obtained through the touch display module, the user input task demand at least includes: the flight height, the endurance time and the load intensity, etc. Key task parameters.

[0032] Based on the above initial acquisition of multi-energy state data and task demand, the controller performs multi-dimensional analysis to determine the initial working mode: if the lithium battery remaining power is sufficient and the task load is low, select the lithium battery mode, if the solar illumination condition is excellent and the task energy consumption is stable, select the solar mode, if the task energy consumption is high or the endurance requirement is long, then start the hybrid power mode, and coordinate the movement of multiple energies; If other energy states are insufficient, switch to the fuel cell mode as the main power supply.

[0033] Subsequently, more detailed running data is obtained in real time through various sensors: the first voltage and the first current output by the fuel cell through the first sensor to reflect the original output characteristics of the fuel cell, the second voltage and the second current output by the first DC / DC converter to reflect the effective output of the fuel cell after optimization, the real-time flow of hydrogen entering the fuel cell through the flow sensor, the third voltage and the third current output by the lithium battery through the third sensor to reflect the actual power supply state of the lithium battery, the fourth voltage and the fourth current output by the solar panel through the fourth sensor to reflect the original power generation capacity of the solar panel, and the fifth voltage and the fifth current output by the second DC / DC converter through the fifth sensor to reflect the effective output of the solar after optimization.

[0034] Based on these real-time collected voltage and current data, the controller performs dynamic calibration and update of the power state: for example, combined with the third voltage and the third current of the lithium battery, the remaining power and other power states of the lithium battery are corrected through the power calculation model. According to the fourth voltage, the fourth current, the fifth voltage and the fifth current of the solar panel, the power generation efficiency and the actual power supply capacity after conversion of the solar panel are comprehensively evaluated, and the power state of the solar panel is updated. Through the first voltage, the first current, the second voltage and the second current of the fuel cell, the power generation efficiency and conversion loss of the fuel cell are analyzed, and the power state of the fuel cell is dynamically updated.

[0035] Meanwhile, based on the real-time hydrogen flow detected by the flow sensor, the hydrogen consumption per unit time and the cumulative hydrogen consumption are calculated in combination with the time parameter. Based on the second voltage and the second current, the actual power output by the fuel cell after optimization by the first DC / DC converter, i.e., the effective power supply, is calculated by voltage, current and time. Finally, the controller determines the hydrogen leakage state by comparing the theoretical corresponding relationship between the hydrogen consumption and the fuel cell output power, i.e., the theoretical power generated by a unit of hydrogen, that is, the theoretical power generated by a unit of hydrogen. If the difference between the actual consumption and the theoretical consumption is within the normal error range, it is determined that there is no leakage; If the difference exceeds the normal range but does not reach the critical value, it is determined that there is a slight leakage; If the difference significantly exceeds the critical value, it is determined that there is a severe leakage, so that the system can trigger an alarm or a protection signal in time.

[0036] By applying the technical solution of the embodiment, the initial working mode suitable for the task can be determined based on multi-dimensional data by initially and accurately collecting the power states of the lithium battery, the solar panel and the fuel cell, and the task requirements input by the user, such as flight altitude, endurance time and load strength, so as to avoid energy mismatch and waste. Subsequently, the voltage and current of the fuel cell and the DC / DC converter, the hydrogen flow, the output parameters of the lithium battery and the solar panel are obtained in real time by the sensors, so that the power states of the energy sources can be dynamically calibrated and updated, the judgment of the energy supply capacity is accurate, and reliable basis is provided for mode adjustment. At the same time, the consumption is calculated based on the hydrogen flow, the effective output power of the fuel cell is calculated based on the voltage and current, and the hydrogen leakage state is determined by comparing the theoretical corresponding relationship between the two, so that the alarm and protection can be triggered in time, the safety of the aircraft operation is ensured, the fine control of energy utilization is realized, the energy utilization efficiency is improved, the endurance is prolonged, and the stable energy supply demand in different task scenarios is adapted.

[0037] Although the embodiments of the present application have been disclosed as above, they are not limited to the applications listed in the specification and the embodiments. It can be fully applied to various fields suitable for the present application. Additional modifications can be easily realized by those skilled in the art. Therefore, the present application is not limited to specific details and the figures shown and described herein without departing from the general concept defined by the claims and the equivalent scope.

Claims

1. An energy management and control system for a fuel cell electric aircraft, characterized in that: include: a fuel cell assembly, the fuel cell assembly being configured to output a first power signal; a first DC / DC converter, wherein a first terminal of the first DC / DC converter is electrically connected to an output terminal of the fuel cell assembly, and the first DC / DC converter is used to perform energy management optimization on the first power signal output by the fuel cell assembly; a lithium battery, wherein the lithium battery is used to output a second power signal; a solar panel, wherein the solar panel is used to output a third power signal; a second DC / DC converter, wherein a first terminal of the second DC / DC converter is electrically connected to an output terminal of the solar panel, and the second DC / DC converter is configured to perform energy management optimization on the second power signal output by the solar panel; an energy management controller, the energy management controller being electrically connected to one end of the lithium battery, the second end of the first DC / DC converter, and the second end of the second DC / DC converter, respectively, the energy management controller being configured to obtain an electrical energy state of the lithium battery, an electrical energy state of the solar panel, an electrical energy state of the fuel cell, and a mission requirement, and determine an operating mode based on the electrical energy state of the lithium battery, the electrical energy state of the solar panel, the electrical energy state of the fuel cell, and the mission requirement, the operating modes including at least a lithium battery mode, a fuel cell mode, a solar mode, and a hybrid power mode; A touch display module is electrically connected to the energy management controller, and is used to obtain task requirement data and also to display the power status of the lithium battery, the power status of the solar panel, and the power status of the fuel cell.

2. The energy management and control system for a fuel cell electric aircraft according to claim 1, characterized in that: The fuel cell assembly comprises: A hydrogen storage bottle having a first output port; a solenoid valve, a first end of which is connected to the first output port, and the solenoid valve is used to control the exhaust volume of hydrogen discharged from the hydrogen storage bottle; a pressure reducing valve, wherein a first end of the pressure reducing valve is connected to a second end of the solenoid valve; A fuel cell, wherein a first end of the fuel cell is connected to a second end of the pressure reducing valve, a second end of the fuel cell is electrically connected to a first end of the first DC / DC converter, and the fuel cell is used to output a first power signal.

3. The energy management and control system for a fuel cell electric aircraft according to claim 2, characterized in that: The control system further comprises: A first sensor is provided on a connection line between the fuel cell and the first DC / DC converter, and is used to detect a first voltage and a first current output by the fuel cell.

4. The energy management and control system for a fuel cell electric aircraft according to claim 2, characterized in that: The control system further comprises: A second sensor is provided on a connection line between the first DC / DC converter and the energy management controller, and is used to detect a second voltage and a second current output by the first DC / DC converter.

5. The energy management and control system for a fuel cell electric aircraft according to claim 2, characterized in that: The fuel cell assembly further comprises: A flow sensor is provided on a pipeline between the pressure reducing valve and the fuel cell, and is used to detect the flow of hydrogen entering the fuel cell.

6. The energy management and control system for a fuel cell electric aircraft according to claim 1, characterized in that: The control system further comprises: A third sensor is provided on the connection line between the lithium battery and the energy management controller, and is used to detect a third voltage and a third current output by the lithium battery.

7. The energy management and control system for a fuel cell electric aircraft according to claim 1, characterized in that: The control system further comprises: A fourth sensor is provided on a connection line between the solar panel and the second DC / DC converter, and is used to detect a fourth voltage and a fourth current output by the solar panel.

8. The energy management and control system for a fuel cell electric aircraft according to claim 7, characterized in that: The control system further comprises: A fifth sensor is provided on a connection line between the second DC / DC converter and the energy management controller, and is used to detect a fifth voltage and a fifth current output by the second DC / DC converter.

9. A method for energy management and control of a fuel cell electric aircraft, characterized in that: An energy management and control system for a fuel cell electric aircraft according to any one of claims 1 to 8, characterized in that it comprises: The energy management controller obtains the power state of the lithium battery, the power state of the solar panel, the power state of the power state, and the mission requirement in response to the electric aircraft startup signal; An operating mode is determined based on the power state of the lithium battery, the power state of the solar panel, the power state of the power state, and the task requirements.

10. The energy management control method for a fuel cell electric aircraft according to claim 9, further comprising: The energy management controller respectively obtains a first voltage and a first current output by the fuel cell, a second voltage and a second current output by the first DC / DC converter, a flow rate of hydrogen entering the fuel cell, a third voltage and a third current output by the lithium battery, a fourth voltage and a fourth current output by the solar panel, and a fifth voltage and a fifth current output by the second DC / DC converter; determining an electrical energy state of the lithium battery, an electrical energy state of the solar panel, and an electrical energy state of the fuel cell based on a first voltage and a first current output by the fuel cell, a second voltage and a second current output by the first DC / DC converter, a third voltage and a third current output by the lithium battery, a fourth voltage and a fourth current output by the solar panel, and a fifth voltage and a fifth current output by the second DC / DC converter; determining hydrogen consumption based on the flow of hydrogen entering the fuel cell; determining an output power of the fuel cell based on the second voltage and the second current; Based on the hydrogen consumption and the power output of the fuel cell, a hydrogen leakage state is determined, where the hydrogen leakage state includes at least: a no leakage state, a slight leakage state, and a severe leakage state.

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