Power supply control method for hydrogen fuel cell unmanned aerial vehicle based on full-power DCDC converter

Abstract

The invention discloses a power supply control method for a hydrogen fuel cell unmanned aerial vehicle based on a full-power DCDC converter, and belongs to the technical field of unmanned aerial vehicle hydrogen fuel cells, 1200 W power voltage stabilization is realized through four LT8708 chips connected in parallel, the working voltage of a galvanic pile is enabled to accord with the working rated voltage of a rotor motor, meanwhile, the parallel connection of the four LT8708 chips is realized through a current sharing circuit, and the working efficiency of the rotor motor is improved. Therefore, it is ensured that each chip evenly distributes load current, the stability and reliability of a system are improved, all the power MOS tubes are distributed on the back face of the power board, heat dissipation is conducted through the cooling fins, the cooling fins make direct contact with the power MOS tubes through heat conduction materials, the heat dissipation efficiency is improved, the overheating problem of the power MOS tubes is effectively avoided, and the service life of the power board is prolonged. Meanwhile, the power supply control method is suitable for hydrogen fuel cell unmanned aerial vehicles of various models, the design meets the weight and size requirements of the unmanned aerial vehicles, and it is ensured that efficient energy management is achieved in a limited space.

Description

Technical Field

[0001] The present invention relates to the technical field of hydrogen fuel cells for unmanned aerial vehicles, and in particular to a power supply control method for hydrogen fuel cell unmanned aerial vehicles based on a full-power DCDC converter. Background Art

[0002] With the advancement of science and technology and the enhancement of environmental awareness, hydrogen fuel cell technology is being used more and more widely in drones. Hydrogen fuel cells have the advantages of high energy density, environmental friendliness, and long endurance, and have become one of the important choices for drone power systems. However, existing hydrogen fuel cell drones still face many challenges in terms of rapid power response, unstable output voltage, and power loss, especially in the case of high power output and long-term continuous operation. Therefore, the design of the power board is crucial. Traditional power board designs often have problems such as insufficient voltage regulation, poor heat dissipation, and inaccurate current and voltage monitoring, which makes it difficult to meet the high performance requirements of hydrogen-powered drones. Therefore, a new type of power board design is urgently needed to make the hydrogen fuel cell system fit perfectly with the drone motor and achieve more efficient and stable energy management. To this end, a power supply control method for hydrogen fuel cell drones based on a full-power DCDC converter is proposed. Summary of the invention

[0003] The object of the present invention is to provide a power supply control method for a hydrogen fuel cell drone based on a full-power DCDC converter to solve the problems raised in the above background technology.

[0004] To achieve the above object, the present invention provides the following technical solution: A power supply control method for a hydrogen fuel cell drone based on a full-power DCDC converter, comprising the following steps:

[0005] S1. Initialization startup: After the drone is powered on, it first performs a self-test to check the status of each chip, the connection of the sensor, the operation of the voltage divider, and the initialization of the functional modules;

[0006] S2, power conversion operation: including input power connection and power distribution and voltage regulation;

[0007] S3, heat dissipation management: including power MOS tube operation and heat dissipation of heat sink;

[0008] S4, auxiliary lithium battery system management: including charging process and discharging process;

[0009] S5, real-time monitoring and data acquisition: including current and voltage sampling, signal conversion, data monitoring and fault diagnosis;

[0010] S6, protection mechanism: including over-current protection, over-voltage protection and over-temperature protection;

[0011] S7, shutdown and power off: including normal shutdown and emergency power off.

[0012] As a further preferred embodiment of the present technical solution: in S1, the chip adopts LT8708 chip, the sensor adopts LTC6102 current sensor, the voltage divider adopts bridge circuit voltage divider, the functional module includes power board, and the power board adopts full power DCDC converter;

[0013] Among them, the voltage is set, and the output voltage of the full-power DCDC converter is set according to the rated voltage of the drone rotor motor.

[0014] As a further preferred embodiment of the technical solution: in S2, the input power supply is connected: the hydrogen fuel cell stack in the drone is used as the main power supply and is connected to the full-power DCDC converter through the input port;

[0015] Power distribution and voltage regulation: Four LT8708 chips are used, and four LT8708 chips are connected in parallel to achieve 1500W power regulation. Among them, each chip evenly distributes the load current to ensure stable output of the system.

[0016] As a further preferred embodiment of the present technical solution: four LT8708 chips are connected in parallel to achieve the DCDC conversion effect, and the current sharing circuit dynamically monitors and adjusts the current distribution of each chip to prevent overload of a single chip.

[0017] As a further preferred embodiment of the present technical solution: during the operation from S1 to S2, four parallel LT8708 chips simultaneously perform a working strategy, and the specific working strategy includes the following steps:

[0018] A1. Initialization startup: Start system initialization and detect the status of all chips;

[0019] A2. Detect load demand: read load current demand and voltage demand;

[0020] A3. Start all chips: When the load demand is greater than 0, start all LT8708 chips;

[0021] A4. Uniform load distribution: Use current balancing circuit to distribute equal current load to each chip;

[0022] A5. Working status monitoring: Real-time monitoring of the current, voltage and temperature of each chip, and adjustment of the current distribution of each chip to maintain current balance;

[0023] A6. Overload protection: When the current or temperature of any chip exceeds the safe range, the protection mechanism is triggered, reducing the power output and sending a warning signal;

[0024] A7. Turn off the computer.

[0025] As a further preferred embodiment of the present technical solution: four LT8708 chips are connected in parallel to dissipate heat evenly, and each chip shares the load current at the same time, thereby reducing the power consumption of each chip and improving the overall heat dissipation performance. Moreover, since each chip works within its optimal efficiency range, the overall efficiency of the system can be effectively improved.

[0026] Among them, the four parallel LT8708 chips can respond quickly. When the load changes, the parallel system can respond quickly without waiting for additional chips to start. At the same time, stress is reduced. Each chip is subjected to less electrical and thermal stress, which helps to extend the service life of the chip.

[0027] As a further preferred embodiment of the technical solution: in S3, the power MOS tube works: the power MOS tube is located at the back of the power board and participates in the DCDC conversion process to generate heat;

[0028] Heat dissipation by heat sink: A heat sink is installed on the power board, and the heat generated by the power MOS tube is transferred to the heat sink through the thermal conductive material;

[0029] The heat sink dissipates heat through convection heat exchange with the surrounding air, thereby ensuring that the power MOS tube operates within a safe temperature range.

[0030] As a further preferred embodiment of the present technical solution: in S4, the auxiliary lithium battery system is used as a backup power source and is connected to the full-power DCDC converter through a dual interface to achieve simultaneous charging and discharging;

[0031] Among them, the charging process: the auxiliary lithium battery system is charged evenly through the charging interface to keep the battery in the best power state;

[0032] Discharge process: When the hydrogen fuel cell stack needs additional power support, the auxiliary lithium battery provides compensatory power through the discharge interface to ensure stable operation of the system.

[0033] As a further preferred embodiment of the technical solution: during the S4 operation, the full-power DCDC converter operates synchronously, and the specific operation steps include:

[0034] B1, standby state;

[0035] B2. Standby power supply: Full-power DCDC converter meets the low power demand in standby state through each LT8708 chip;

[0036] B3. Takeoff power supply: The hydrogen fuel cell stack and full-power DCDC converter provide the main power to meet the high power demand for takeoff. At the same time, the auxiliary lithium battery provides additional power through the discharge interface to ensure sufficient power supply during takeoff.

[0037] B4. Cruise power supply: The full-power DCDC converter provides the power required for cruise, which is less than 1500W. While meeting the cruise power demand, the remaining power is used to charge the lithium battery and balanced charging is performed through the charging interface;

[0038] B5. Dealing with sudden changes: When encountering sudden changes in wind speed during cruising, the power demand suddenly increases. The full-power DCDC converter and lithium battery provide additional power at the same time to ensure stable cruising of the drone.

[0039] B6. Landing status: Confirm the power required for landing, which is usually less than 1500W. The full-power DCDC converter provides the low power required for landing.

[0040] As a further preferred embodiment of the present technical solution: in S5, current and voltage sampling: the current and voltage of the battery stack, the lithium battery and the load are monitored in real time through the LTC6102 current sensor and the bridge circuit voltage divider;

[0041] Signal conversion: The sampled current and voltage signals are converted into 1V-5V analog signals and transmitted to the drone’s built-in control system;

[0042] Data monitoring and fault diagnosis: The control system analyzes analog signals, monitors system status, and performs fault diagnosis to ensure the normal operation of the system.

[0043] As a further preferred embodiment of the present technical solution: in S6, overcurrent protection: when the system detects that the current exceeds the safety threshold, the overcurrent protection circuit will immediately cut off the power supply to prevent system damage;

[0044] Overvoltage protection: When the system voltage exceeds the safe range, the overvoltage protection circuit will start to reduce the voltage to prevent system failure;

[0045] Over-temperature protection: When the system temperature exceeds the safe range, the over-temperature protection circuit will take cooling measures to ensure that the system operates within the safe temperature range.

[0046] As a further preferred embodiment of the technical solution: in S7, normal shutdown: when the task is completed or the system needs to be shut down, the control system gradually reduces the load according to a predetermined procedure, shuts down various mechanisms, and ensures safe power off;

[0047] Emergency power off: In case of irrecoverable faults or emergencies, the system will implement emergency power off through protection circuits to prevent damage and accidents.

[0048] Compared with the prior art, the present invention has the following beneficial effects:

[0049] 1. In the present invention, 1500W power voltage stabilization is achieved by connecting four LT8708 chips in parallel, so that the working voltage of the battery stack meets the working rated voltage of the rotor motor. At the same time, the parallel connection of the four LT8708 chips is achieved through a current sharing circuit, thereby ensuring that each chip evenly distributes the load current, thereby improving the stability and reliability of the system;

[0050] 2. In the present invention, all power MOS tubes are distributed on the back of the power board and dissipate heat through a heat sink. The heat sink is in direct contact with the power MOS tube through a thermally conductive material, thereby improving heat dissipation efficiency and effectively avoiding the overheating problem of the power MOS tube, thereby ensuring stable operation of the system under high load;

[0051] 3. The auxiliary lithium battery of the hydrogen fuel cell system of the present invention is charged and discharged simultaneously through a dual interface, which includes a charging interface and a discharging interface. The charging interface charges the lithium battery system evenly, and the discharging interface is connected to the power system of the drone to dynamically compensate the hydrogen fuel cell stack to ensure the stability and reliability of the system.

[0052] 4. The current and voltage of all power components (battery stack, lithium battery, load) in the present invention are sampled, converted into 1V-5V analog signals and transmitted to the sampling interface. The sampling includes LTC6102 current sensor and bridge circuit voltage divider, which respectively monitor the current and voltage of the battery stack, lithium battery and load in real time. The sampling interface transmits the 1V-5V analog signal to the control system of the drone for data monitoring and fault diagnosis;

[0053] 5. At the same time, the power board of the present invention integrates protection circuits, including overcurrent protection, overvoltage protection and overtemperature protection, which improves the safety and reliability of the system. The power control method of the present invention is applicable to various types of hydrogen fuel cell drones, and the design meets the weight and volume requirements of the drone, ensuring efficient energy management in a limited space;

[0054] 6. In combination with 1-5, the present invention provides a power control method for a hydrogen fuel cell UAV based on a full-power DCDC converter, which solves the deficiencies in the prior art and improves the performance and reliability of the UAV. The power control method of the present invention is not only adaptable to various types of hydrogen fuel cell UAVs, but also has efficient voltage stabilization, excellent heat dissipation management, real-time current and voltage monitoring, and complete protection measures, meeting the needs of modern UAVs for high-performance power management systems. BRIEF DESCRIPTION OF THE DRAWINGS

[0055] Figure 1 It is a flow chart of a power supply control method for a hydrogen fuel cell drone based on a full-power DCDC converter according to the present invention;

[0056] Figure 2It is a schematic diagram of the architecture of the power supply control method for hydrogen fuel cell drone based on full-power DCDC converter of the present invention;

[0057] Figure 3 It is a schematic diagram of the process structure of the working strategy of four parallel LT8708 chips in the power supply control method for hydrogen fuel cell drone based on full-power DCDC converter of the present invention;

[0058] Figure 4 The present invention is a schematic diagram of the operation flow of the full-power DCDC converter in the power supply control method for a hydrogen fuel cell drone based on the full-power DCDC converter. DETAILED DESCRIPTION

[0059] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the accompanying drawings in the embodiments of the present invention.

[0060] Example 1

[0061] See also Figure 1-Figure 4 The present invention provides a technical solution: a power supply control method for a hydrogen fuel cell drone based on a full-power DCDC converter, comprising the following steps:

[0062] S1. Initialization startup: After the drone is powered on, it first performs a self-test to check the status of each chip, the connection of the sensor, the operation of the voltage divider, and the initialization of the functional modules;

[0063] S2, power conversion operation: including input power connection and power distribution and voltage regulation;

[0064] S3, heat dissipation management: including power MOS tube operation and heat dissipation of heat sink;

[0065] S4, auxiliary lithium battery system management: including charging process and discharging process;

[0066] S5, real-time monitoring and data acquisition: including current and voltage sampling, signal conversion, data monitoring and fault diagnosis;

[0067] S6, protection mechanism: including over-current protection, over-voltage protection and over-temperature protection;

[0068] S7, shutdown and power off: including normal shutdown and emergency power off.

[0069] In this embodiment, specifically: in S1, the chip uses the LT8708 chip, the sensor uses the LTC6102 current sensor, the voltage divider uses a bridge circuit voltage divider, the functional module includes a power board, and the power board uses a full-power DCDC converter;

[0070] Among them, the voltage is set, and the output voltage of the full-power DCDC converter is set according to the rated voltage of the drone rotor motor.

[0071] In this embodiment, specifically: in S2, the input power supply is connected: the hydrogen fuel cell stack in the drone is used as the main power supply and is connected to the full-power DCDC converter through the input port;

[0072] Power distribution and voltage regulation: Four LT8708 chips are used, and four LT8708 chips are connected in parallel to achieve 1500W power regulation. Among them, each chip evenly distributes the load current to ensure stable output of the system.

[0073] In this embodiment, specifically: four LT8708 chips are connected in parallel to achieve the DCDC conversion effect, and the current sharing circuit dynamically monitors and adjusts the current distribution of each chip to prevent a single chip from being overloaded.

[0074] In this embodiment, specifically: during the operation from S1 to S2, four parallel LT8708 chips simultaneously perform a working strategy, and the specific working strategy includes the following steps:

[0075] A1. Initialization startup: Start system initialization and detect the status of all chips;

[0076] A2. Detect load demand: read load current demand and voltage demand;

[0077] A3. Start all chips: When the load demand is greater than 0, start all LT8708 chips;

[0078] A4. Uniform load distribution: Use current balancing circuit to distribute equal current load to each chip;

[0079] A5. Working status monitoring: Real-time monitoring of the current, voltage and temperature of each chip, and adjustment of the current distribution of each chip to maintain current balance;

[0080] A6. Overload protection: When the current or temperature of any chip exceeds the safe range, the protection mechanism is triggered, reducing the power output and sending a warning signal;

[0081] A7. Turn off the computer.

[0082] In this embodiment, specifically: in S3, the power MOS tube works: the power MOS tube is located at the back of the power board and participates in the DCDC conversion process to generate heat;

[0083] Heat dissipation by heat sink: A heat sink is installed on the power board, and the heat generated by the power MOS tube is transferred to the heat sink through the thermal conductive material;

[0084] The heat sink dissipates heat through convection heat exchange with the surrounding air, thereby ensuring that the power MOS tube operates within a safe temperature range.

[0085] In this embodiment, specifically: in S4, the auxiliary lithium battery system is used as a backup power source and is connected to the full-power DCDC converter through a dual interface to achieve simultaneous charging and discharging;

[0086] Among them, the charging process: the auxiliary lithium battery system is charged evenly through the charging interface to keep the battery in the best power state;

[0087] Discharge process: When the hydrogen fuel cell stack needs additional power support, the auxiliary lithium battery provides compensatory power through the discharge interface to ensure stable operation of the system.

[0088] In this embodiment, specifically: during the S4 operation, the full-power DCDC converter operates synchronously, and the specific operation steps include:

[0089] B1, standby state;

[0090] B2. Standby power supply: Full-power DCDC converter meets the low power demand in standby state through each LT8708 chip;

[0091] B3. Takeoff power supply: The hydrogen fuel cell stack and full-power DCDC converter provide the main power to meet the high power demand for takeoff. At the same time, the auxiliary lithium battery provides additional power through the discharge interface to ensure sufficient power supply during takeoff.

[0092] B4. Cruise power supply: The full-power DCDC converter provides the power required for cruise, which is less than 1500W. While meeting the cruise power demand, the remaining power is used to charge the lithium battery and balanced charging is performed through the charging interface;

[0093] B5. Dealing with sudden changes: When encountering sudden changes in wind speed during cruising, the power demand suddenly increases. The full-power DCDC converter and lithium battery provide additional power at the same time to ensure stable cruising of the drone.

[0094] B6. Landing status: Confirm the power required for landing, which is usually less than 1500W. The full-power DCDC converter provides the low power required for landing.

[0095] In this embodiment, specifically: in S5, current and voltage sampling: the current and voltage of the battery stack, lithium battery and load are monitored in real time through the LTC6102 current sensor and the bridge circuit voltage divider;

[0096] Signal conversion: The sampled current and voltage signals are converted into 1V-5V analog signals and transmitted to the drone’s built-in control system;

[0097] Data monitoring and fault diagnosis: The control system analyzes analog signals, monitors system status, and performs fault diagnosis to ensure the normal operation of the system.

[0098] In this embodiment, specifically: in S6, overcurrent protection: when the system detects that the current exceeds the safety threshold, the overcurrent protection circuit will immediately cut off the power supply to prevent system damage;

[0099] Overvoltage protection: When the system voltage exceeds the safe range, the overvoltage protection circuit will start to reduce the voltage to prevent system failure;

[0100] Over-temperature protection: When the system temperature exceeds the safe range, the over-temperature protection circuit will take cooling measures to ensure that the system operates within the safe temperature range.

[0101] In this embodiment, specifically: in S7, normal shutdown: when the task is completed or the system needs to be shut down, the control system gradually reduces the load according to a predetermined procedure, shuts down various mechanisms, and ensures safe power off;

[0102] Emergency power off: In case of irrecoverable faults or emergencies, the system will implement emergency power off through protection circuits to prevent damage and accidents.

[0103] Example 2

[0104] See also Figure 3 , a power control method for hydrogen fuel cell drones based on full-power DCDC converter: four parallel LT8708 chips perform a working strategy, and the specific working strategy includes the following steps:

[0105] A1. Initialization startup: Start system initialization and detect the status of all chips;

[0106] A2. Detect load demand: read load current demand and voltage demand;

[0107] A3. Start all chips: When the load demand is greater than 0, start all LT8708 chips;

[0108] A4. Uniform load distribution: Use current balancing circuit to distribute equal current load to each chip;

[0109] A5. Working status monitoring: Real-time monitoring of the current, voltage and temperature of each chip, and adjustment of the current distribution of each chip to maintain current balance;

[0110] A6. Overload protection: When the current or temperature of any chip exceeds the safe range, the protection mechanism is triggered, reducing the power output and sending a warning signal;

[0111] A7. Turn off the computer.

[0112] In this embodiment, specifically: four LT8708 chips are connected in parallel to work, which can dissipate heat evenly, and each chip shares the load current at the same time, thereby reducing the power consumption of each chip and improving the overall heat dissipation performance. Moreover, since each chip works within its optimal efficiency range, the overall efficiency of the system can be effectively improved;

[0113] Among them, the four parallel LT8708 chips can respond quickly. When the load changes, the parallel system can respond quickly without waiting for additional chips to start. At the same time, stress is reduced. Each chip is subjected to less electrical and thermal stress, which helps to extend the service life of the chip.

[0114] See also Figure 4 , a power supply control method for a hydrogen fuel cell drone based on a full-power DCDC converter: The full-power DCDC converter operates, and its specific operating steps include:

[0115] B1, standby state;

[0116] B2. Standby power supply: Full-power DCDC converter meets the low power demand in standby state through each LT8708 chip;

[0117] B3. Takeoff power supply: The hydrogen fuel cell stack and full-power DCDC converter provide the main power to meet the high power demand for takeoff. At the same time, the auxiliary lithium battery provides additional power through the discharge interface to ensure sufficient power supply during takeoff.

[0118] B4. Cruise power supply: The full-power DCDC converter provides the power required for cruise, which is less than 1500W. While meeting the cruise power demand, the remaining power is used to charge the lithium battery and balanced charging is performed through the charging interface;

[0119] B5. Dealing with sudden changes: When encountering sudden changes in wind speed during cruising, the power demand suddenly increases. The full-power DCDC converter and lithium battery provide additional power at the same time to ensure stable cruising of the drone.

[0120] B6. Landing state: Confirm the power required for landing, which is usually less than 1500W. The full-power DCDC converter provides the low power required for landing.

[0121] Working principle: Four LT8708 chips are connected in parallel to achieve 1500W power stabilization. LT8708 is a high-efficiency DCDC converter chip with high conversion efficiency and stable output performance. By connecting four LT8708 chips in parallel, stable voltage output can be achieved under high power output conditions to meet the working rated voltage requirements of the UAV rotor motor. In order to ensure that the four LT8708 chips evenly distribute the load current, a current balancing circuit design is adopted. The current balancing circuit can monitor the current distribution of each chip in real time and make dynamic adjustments to avoid overloading of a single chip, thereby improving the stability and reliability of the system.

[0122] At the same time, all power MOS tubes are distributed on the back of the power board, so that the space on the back can be effectively used for heat dissipation. The power MOS tube is an important part of the full-power DCDC converter. It will generate a lot of heat when working. A heat sink is installed on the power board. The heat conductive material is in direct contact with the power MOS tube. The heat conductive material can efficiently transfer the heat generated by the MOS tube to the heat sink. The heat sink dissipates the heat through convection heat exchange with the surrounding air, thereby improving the heat dissipation efficiency and ensuring the stable operation of the system under high load;

[0123] The auxiliary lithium battery of the hydrogen fuel cell system is charged and discharged simultaneously through dual interfaces, which include a charging interface and a discharging interface. The charging interface is used to evenly charge the lithium battery to ensure that the lithium battery maintains the best power state during use. The discharging interface is connected to the power system of the drone to dynamically compensate the hydrogen fuel cell stack. When the hydrogen fuel cell stack is outputting at high power, the auxiliary lithium battery can provide additional power support to ensure the stability and reliability of the system.

[0124] At the same time, the LTC6102 current sensor and bridge circuit voltage divider are used to monitor the current and voltage of the battery stack, lithium battery and load in real time. The LTC6102 current sensor has the characteristics of high precision and low power consumption, and is suitable for use in application scenarios such as drones that have strict requirements on weight and power consumption.

[0125] All sampled current and voltage signals are converted into 1V-5V analog signals and transmitted to the UAV control system through the sampling interface. The control system can monitor these signals in real time, perform data analysis and fault diagnosis, and improve the intelligence level and reliability of the system.

[0126] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A power supply control method for a hydrogen fuel cell drone based on a full-power DCDC converter, characterized in that: The following steps are involved: S1. Initialization startup: After the drone is powered on, it first performs a self-test to check the status of each chip, the connection of the sensor, the operation of the voltage divider, and the initialization of the functional modules; S2, power conversion operation: including input power connection and power distribution and voltage regulation; S3, heat dissipation management: including power MOS tube operation and heat dissipation of heat sink; S4, auxiliary lithium battery system management: including charging process and discharging process; S5, real-time monitoring and data acquisition: including current and voltage sampling, signal conversion, data monitoring and fault diagnosis; S6, protection mechanism: including over-current protection, over-voltage protection and over-temperature protection; S7, shutdown and power off: including normal shutdown and emergency power off.

2. The power supply control method for a hydrogen fuel cell drone based on a full-power DCDC converter according to claim 1 is characterized in that: In S1, the chip uses the LT8708 chip, the sensor uses the LTC6102 current sensor, the voltage divider uses a bridge circuit voltage divider, and the functional module includes a power board, which uses a full-power DCDC converter.

3. The power control method for a hydrogen fuel cell drone based on a full-power DCDC converter according to claim 2 is characterized in that: In S2, the input power connection: the hydrogen fuel cell stack in the drone is used as the main power source and is connected to the full-power DCDC converter through the input port; Power distribution and voltage regulation: Four LT8708 chips are used, and four LT8708 chips are connected in parallel to achieve 1500W power regulation.

4. The power supply control method for a hydrogen fuel cell drone based on a full-power DCDC converter according to claim 3 is characterized in that: During the operation from S1 to S2, the four parallel LT8708 chips simultaneously perform the working strategy, which includes the following steps: A1. Initialization startup: Start system initialization and detect the status of all chips; A2. Detect load demand: read load current demand and voltage demand; A3. Start all chips: When the load demand is greater than 0, start all LT8708 chips; A4. Uniform load distribution: Use current balancing circuit to distribute equal current load to each chip; A5. Working status monitoring: Real-time monitoring of the current, voltage and temperature of each chip, and adjustment of the current distribution of each chip to maintain current balance; A6. Overload protection: When the current or temperature of any chip exceeds the safe range, the protection mechanism is triggered, reducing the power output and sending a warning signal; A7. Turn off the computer.

5. The power control method for a hydrogen fuel cell drone based on a full-power DCDC converter according to claim 2, characterized in that: In S3, the power MOS tube works: the power MOS tube is located on the back of the power board and participates in the DCDC conversion process, generating heat; Heat dissipation by heat sink: A heat sink is installed on the power board, and the heat generated by the power MOS tube is transferred to the heat sink through the thermal conductive material.

6. The power supply control method for a hydrogen fuel cell drone based on a full-power DCDC converter according to claim 1 is characterized in that: In S4, the auxiliary lithium battery system is used as a backup power source and is connected to the full-power DCDC converter through dual interfaces to achieve simultaneous charging and discharging; Among them, the charging process: the auxiliary lithium battery system is charged evenly through the charging interface to keep the battery in the best power state; Discharge process: When the hydrogen fuel cell stack needs additional power support, the auxiliary lithium battery provides compensatory power through the discharge interface to ensure stable operation of the system.

7. The power supply control method for a hydrogen fuel cell drone based on a full-power DCDC converter according to claim 6 is characterized in that: During S4 operation, the full-power DCDC converter operates synchronously, and the specific operation steps include: B1, standby state; B2. Standby power supply: Full-power DCDC converter meets the low power demand in standby state through each LT8708 chip; B3. Takeoff power supply: The hydrogen fuel cell stack and full-power DCDC converter provide the main power to meet the high power demand for takeoff. At the same time, the auxiliary lithium battery provides additional power through the discharge interface to ensure sufficient power supply during takeoff. B4. Cruise power supply: The full-power DCDC converter provides the power required for cruise, which is less than 1500W. While meeting the cruise power demand, the remaining power is used to charge the lithium battery and balanced charging is performed through the charging interface; B5. Dealing with sudden changes: When encountering sudden changes in wind speed during cruising, the power demand suddenly increases. The full-power DCDC converter and lithium battery provide additional power at the same time to ensure stable cruising of the drone. B6. Landing state: Confirm the power required for landing, which is usually less than 1500W. The full-power DCDC converter provides the low power required for landing.

8. The power control method for a hydrogen fuel cell drone based on a full-power DCDC converter according to claim 2 is characterized in that: In S5, current and voltage sampling: the current and voltage of the battery stack, lithium battery and load are monitored in real time through the LTC6102 current sensor and the bridge circuit voltage divider; Signal conversion: The sampled current and voltage signals are converted into 1V-5V analog signals and transmitted to the drone’s built-in control system; Data monitoring and fault diagnosis: The control system analyzes analog signals, monitors system status, and performs fault diagnosis to ensure the normal operation of the system.

9. The power control method for a hydrogen fuel cell drone based on a full-power DCDC converter according to claim 1, characterized in that: In S6, overcurrent protection: When the system detects that the current exceeds the safety threshold, the overcurrent protection circuit will immediately cut off the power supply to prevent system damage; Overvoltage protection: When the system voltage exceeds the safe range, the overvoltage protection circuit will start to reduce the voltage to prevent system failure; Over-temperature protection: When the system temperature exceeds the safe range, the over-temperature protection circuit will take cooling measures to ensure that the system operates within the safe temperature range.

10. The power control method for a hydrogen fuel cell drone based on a full-power DCDC converter according to claim 1, characterized in that: In S7, normal shutdown: when the task is completed or the system needs to be shut down, the control system gradually reduces the load according to the predetermined procedure, shuts down various mechanisms, and ensures safe power outage; Emergency power off: In case of irrecoverable faults or emergencies, the system will implement emergency power off through protection circuits to prevent damage and accidents.

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