2743 results about "Hydrogen fuel" patented technology

The invention discloses a hydrogen fuel cell production management method and system based on a digital twinning technology, and relates to the technical field of digital twinning, and the method comprises the steps: collecting the production data of a hydrogen fuel cell in real time, carrying out the data preprocessing, and generating standardized data; based on the standardized data, constructing a digital twinborn model by utilizing finite element analysis and a computational fluid dynamics strategy, and training the digital twinborn model through historical data; building a reinforcement learning environment based on the trained digital twinborn model, defining a reinforcement learning agent, and generating an optimal control strategy; production parameters are adjusted according to the optimal control strategy, production data are fed back through the digital twinborn model, the optimization effect is verified regularly, and the digital twinborn model and the optimal control strategy are iteratively updated. According to the method, the optimal strategy is autonomously learned in the simulation environment through the reinforcement learning agent, the generated control strategy can dynamically adjust production parameters, efficiency is improved, energy consumption is reduced, quality is improved, and intelligent decision making and control are achieved.

To provide a system, a method, and an application for carbon recovery system for compact type vessel based on connection between methanol reforming and high-efficiency membrane separation.SOLUTION: Propulsive power is supplied to a vessel by using a methanol aqueous solution as a raw material through steps such as reforming, separation of a reformate product, and hydrogen combustion, hydrogen fuel is manufactured through methanol steam reforming, anxiety about safety of high pressure hydrogen storage in a prior art is eliminated, efficient carbon recovery is carried out by storing separated carbon dioxide by compression and liquefying, heat is supplied for methanol steam reforming and preheating of the fuel by using excess heat of discharged flue gas, and comprehensive use of energy is achieved. Use of hydrogen energy is realized by a vessel without requiring storage and transportation of hydrogen, and a shipping industry contributes to green, low carbon, and sustainable development.SELECTED DRAWING: Figure 1

The invention provides a hydrogen fuel cell hybrid power unmanned aerial vehicle energy adaptive optimization system and method. The system and method aim at achieving adaptive optimization when multiple uncertain factors exist in the flight process of an unmanned aerial vehicle. Through mechanical analysis of the typical flight profile of the unmanned aerial vehicle, an estimation model of load demand power in each stage in the flight process of the unmanned aerial vehicle is constructed. The core of the method is that the flight process of the unmanned aerial vehicle is modeled as a Markov decision process, and a self-adaptive optimization model composed of a power energy consumption state space, a power supply power distribution action space, a reward function, an electric energy supply constraint condition and the like is reasonably constructed. And for an electric energy distribution reward function, a near-end strategy optimization algorithm is applied to train an intelligent agent to continuously update an actor network and iterative learning to approach an expected control strategy, so that self-adaptive intelligent optimal distribution of the hydrogen energy and the electric energy by the hydrogen fuel hybrid power unmanned aerial vehicle energy management system is realized, and a system implementation scheme is provided.

The invention discloses a hydrogen fuel engine electronic thermostat heating assembly control method based on the Internet of Things, particularly relates to the technical field of hydrogen fuel engine control, and is used for solving the problems of cooling response lag and action conflict caused by disconnection of control logic and a real-time network state of an existing temperature control system in a dynamic network environment. Electronic thermostat temperature data and network state data are collected in real time to generate a dynamic synchronization coefficient, network topology toughness evaluation and causal influence analysis are combined to predict instruction conflict areas and divide priorities, and gradient correction is performed on heating power and valve opening based on a target deviation compensation value. And a correction instruction is issued through the distributed control unit and a communication reliability weight is synchronously updated, so that dynamic coordination of a network state and a temperature control parameter is realized, and efficient and stable operation of the hydrogen fuel engine under a complex working condition is ensured.

A heat exchanger system for an aircraft comprises nacelle having an inlet and an outlet, a nacelle heat exchanger within the nacelle, and a fan system within the nacelle. Air flows into the nacelle through the inlet and out of the nacelle through the outlet. The nacelle heat exchanger is configured to transfer heat away from a coolant using the air in an airflow to the nacelle heat exchanger. The fan system is configured to increase the airflow to the nacelle heat exchanger.

The invention relates to the field of hydrogen fuel cells, in particular to a hydrogen fuel cell stack stacking device with an alignment function. The single battery stacking device is applied to stacking of a plurality of single batteries and comprises a conveying mechanism and a material carrying table capable of moving in the vertical direction, a fixing frame is arranged over the material carrying table, a pair of supporting pieces for supporting the single batteries are arranged on the fixing frame, the supporting pieces can horizontally move on the fixing frame, and an alignment discharging mechanism is further arranged on the fixing frame. The alignment discharging mechanism comprises a downward pressing assembly and limiting plates evenly distributed on the periphery of the fixing frame, and the downward pressing assembly is provided with first linkage pieces matched with the limiting plates and second linkage pieces matched with the supporting pieces. Through linkage cooperation of the first linkage piece and the limiting plate, a centering alignment channel with stacked single batteries as the reference is formed, it is ensured that the single batteries to be stacked are accurately positioned, meanwhile, the supporting piece is driven by the second linkage piece to be stably disengaged, and seamless transition from supporting to limiting is achieved.

The invention provides a method for constructing a thickened flame surface model of hydrogen turbulent combustion, which belongs to the technical field of hydrogen fuel engines, and specifically comprises the following steps: modeling a diffusion enhancement effect and a flame surface wrinkle effect caused by multi-scale turbulent flow by constructing a hydrogen fuel turbulent flame speed scale rate under a wide working condition; and the combustion process of the hydrogen fuel can be described more accurately. In addition, on the basis of a thin reaction zone combustion mode, key physical quantities are extracted, a combustion efficiency function is optimized, multi-scale turbulence and a difference diffusion effect are considered, and the thickened flame surface model is further perfected. The development of the method provides powerful technical support for the forward design of the hydrogen fuel engine based on numerical simulation, promotes the engineering application of the hydrogen fuel engine, and assists the hydrogen fuel engine to play a greater role in efficient, clean and safe energy transformation.

The invention relates to the technical field of hydrogen fuel cells, in particular to a high-power hydrogen fuel cell with an efficient heat dissipation structure. Comprising a limiting module, and the limiting module is provided with a plurality of groups of limiting bins capable of installing the hydrogen fuel cell, and a leading-in channel and a leading-out channel capable of leading a cooling medium into the limiting bins and leading the cooling medium out of the limiting bins respectively; the cooling module is fixedly arranged at the top of the limiting module, the output end of the cooling module communicates with the leading-in channel, and the cooling module is used for inputting a cooling medium into the leading-in channel; the heat dissipation module is installed in the limiting module in an embedded mode, and the heat dissipation module is composed of a plurality of sets of heat dissipation frames which are spliced with one another; each heat dissipation frame is provided with a lead-in port and a lead-out port which are used for leading in and leading out a cooling medium; heat energy can be effectively gathered, and dynamic heat dissipation can be conducted according to the use state.

The invention discloses an extended-range hydrogen fuel power ship propulsion system, which relates to the technical field of ship propulsion and comprises an acquisition module, a quantum annealing optimization module and a quantum chip, the acquisition module is used for eliminating noise interference of acquired hydrogen energy ship power parameters through a Kalman filtering algorithm and generating a standardized data packet, and the quantum chip is used for receiving the standardized data packet and outputting the standardized data packet. The method comprises the following steps: mapping hydrogen energy ship power parameters into an Isin model, generating a control instruction according to a hydrogen fuel consumption rate, an equipment life attenuation coefficient and a navigation task priority weight, inputting the control instruction into a simulation model of a proton exchange membrane by a proton membrane regulation and control module, and dynamically regulating a hydrogen production rate and fuel cell power, according to the system, the efficient hydrogen energy closed-loop monitoring unit and the three-level safety protocol are adopted, the response speed and precision are improved, the stability and safety are remarkably enhanced, it is ensured that a ship can reliably operate under the complex working condition, and potential safety risks are reduced.

The invention relates to the technical field of gas turbine engines, and discloses a concentric circle type pure hydrogen combustion micro-mixing combustion chamber head which is characterized in that a combustion bowl is arranged on a secondary hydrogen fuel nozzle, secondary hydrogen fuel realizes stable combustion of hydrogen in a low-working-condition central area on the downstream of the combustion bowl, and a stable low-speed central backflow area is formed on the leeside of the combustion bowl; and the central backflow area ensures good combustion stability of the secondary stage. Main-stage hydrogen fuel sprayed out of the inner ring radial spraying holes and the outer ring radial spraying holes is micro-premixed with incoming flow air, the effect of improving the mixing quality and spatial distribution uniformity of the hydrogen fuel in the premixing process is achieved, and the problem of backfire during combustion of the main-stage hydrogen fuel can be avoided; and meanwhile, a low-speed and relatively-large-scale large annular backflow vortex structure is formed on the leeward side of the V-shaped ring, stable combustion is carried out in the large annular backflow vortex, and therefore the stability and uniformity of main-stage hydrogen combustion are improved, and NOx emission is reduced.

The invention belongs to the technical field of unmanned aerial vehicles, and discloses a hydrogen-lithium hybrid power unmanned aerial vehicle and a control system and a control method thereof. The control system of the hydrogen-lithium hybrid power unmanned aerial vehicle comprises a control unit, and a power supply control module, a temperature control module, a gas control module and an exhaust module which are in communication connection with the control unit, wherein the power supply control module collects the power supply quantity of a hydrogen fuel cell and a lithium battery and controls and distributes the power supply quantity to drive the unmanned aerial vehicle to start and fly; the temperature control module is used for radiating and cooling the hydrogen fuel cell; the gas control module is used for detecting hydrogen pressure and controlling hydrogen flow; the exhaust module is used for controlling exhaust of the hydrogen fuel cell. According to the method, the power supply quantity of the hydrogen fuel cell and the lithium battery is optimally controlled and distributed in the flight control process of the unmanned aerial vehicle, so that the problem of different requirements of the unmanned aerial vehicle on energy in the rapid starting and flight processes is solved, the energy utilization efficiency of the hydrogen-lithium hybrid power unmanned aerial vehicle is improved, and the application range of the hydrogen fuel cell on the unmanned aerial vehicle is expanded.

The invention relates to the technical field of battery heat dissipation, in particular to a hydrogen fuel cell high-uniformity radiator and a high-uniformity heat dissipation method.The hydrogen fuel cell high-uniformity radiator comprises a mounting frame and a heat dissipation box fixed to the side wall of the mounting frame, a heat dissipation cavity is formed between the heat dissipation box and the mounting frame, and a fan is fixed to the end, away from the mounting frame, of the heat dissipation box; the multiple heat dissipation fins are fixed to the mounting frame and distributed at equal intervals, and heat dissipation structures used for disturbing flowing of airflow are arranged on the heat dissipation fins; the air guide mechanism is arranged in the heat dissipation box, a first air guide plate is connected to the air guide mechanism, a follow-up pressurization mechanism is further arranged in the heat dissipation box, a second air guide plate is connected to the follow-up pressurization mechanism, and by controlling the first air guide plate and the second air guide plate to execute deflection action, pressurization airflow can be conveyed to an edge weak air area, so that the pressurization effect is improved; therefore, heat flow escaping from the central area can be smoothly discharged from the edge area.

The invention relates to the technical field of hydrogen energy aviation, and discloses a hydrogen energy aviation fuel storage-supply system and method based on solid hydrogen storage, and the hydrogen energy aviation fuel storage-supply system and method based on solid hydrogen storage are characterized in that the hydrogen release amount adjusting range of a hydrogen storage material is matched with the hydrogen fuel demand adjusting range of a power device by adjusting the hydrogen release catalytic reaction environment temperature of the solid hydrogen storage material; by adopting the pressure stabilizing device, the problem of flow and pressure fluctuation caused by hysteresis of hydrogen release adjustment is solved, and hydrogen release flow adjustment and engine throttling control can be carried out through the thrust rod.

An integrated hydrogen-electric engine includes, an air compressor system; a hydrogen fuel source; a fuel cell; an elongated shaft connected to the air compressor system or a propulsor; and a motor assembly disposed in electrical communication with the fuel cell, wherein the air compressor system includes a plurality of electrically driven compressors configured to run in series or parallel.

The present disclosure provides active venting control systems for use with liquid hydrogen tanks. The active venting control system allows a greater mass of hydrogen to be safely stored for a greater period of time. The systems is configured to actively monitor, control, and vent hydrogen based on a combination of pressure and fill level within the tank. When the tank reaches a predetermined fill level, the active venting control system is configured to vent the tank for a predetermined period of time. The active venting control system is configured to repeat the process during a transit and storage time, allowing the tank to be filled with a higher initial fill level and hold a greater mass of hydrogen compared to passive pressure relief systems.

The invention relates to a clean energy combustion technology, and aims to provide a rotational flow on-duty multi-element micro-mixing coupling type low-nitrogen combustion device for hydrogen-doped natural gas. Comprising an air cooling cavity, an air bin fixing cavity and a gas bin fixing cavity which are sequentially stacked from top to bottom. An on-duty combustion unit of a sleeve structure is arranged in the center of the burner in a penetrating mode, and micro-mixing combustion units, independent air bins and independent fuel gas bins are evenly arranged in the circumferential direction in a surrounding mode. A plurality of micro-mixing spray pipes are arranged in an air cooling sleeve of the micro-mixing combustion unit in the axial direction in an array mode, and fuel spray pipes are arranged on a second fixed disc in the axial direction in an array mode. The closed end of the fuel spray pipe extends into the micro-mixing spray pipe corresponding to the fuel spray pipe, and a fuel gas inlet is formed in the bottom of the fuel gas bin fixing cavity. After external air is introduced through an air circulation path from top to bottom to cool the head of the combustor, the heated air is mixed with fuel for combustion, and safe, efficient and low-emission application of natural gas large-proportion hydrogen-doped fuel is achieved.

A fuel cell system includes: a gas turbine having a combustion chamber and a turbine; a hydrogen fuel cell configured to generate electrical energy from input air and input hydrogen; an air flow path for providing air from a source of fresh air as input air to the fuel cell and to the combustion chamber; and a closed hydrogen loop for providing hydrogen from a liquid or compressed hydrogen source to the fuel cell and to the combustion chamber. The system further includes: a hydrogen recirculation loop receiving hydrogen from the liquid or compressed hydrogen source and hydrogen used by the fuel cell to provide cooled used hydrogen, The hydrogen recirculation loop combines the cooled used hydrogen with hydrogen from the liquid or compressed hydrogen source to provide to the fuel cell as the input hydrogen.

A system includes a controller communicably coupled to a hydrogen fueled internal combustion engine. The controller includes at least one processor coupled to at least one memory device storing instructions that, when executed by the at least one processor, cause the controller to perform operations. The operations include receiving an engine shutdown request and responsive to receiving the engine shutdown request, executing an engine shutdown procedure including causing the engine to continue to rotate for at least a predetermined number of rotations or at least a predetermined time period.

A fuel system for a gas turbine engine. The fuel system comprises a fuel offtake configured to divert a portion of hydrogen fuel from a main fuel conduit, a burner configured to burn the portion of hydrogen fuel diverted from the main fuel conduit and at least first and second heat exchangers. The first heat exchanger is configured to transfer heat from exhaust gasses produced by the burner to hydrogen fuel in the main fuel conduit and the second heat exchanger is provided upstream in hydrogen flow of the first heat exchanger and is configured to transfer heat from a further heat exchange fluid to hydrogen fuel in the main fuel conduit. In an embodiment, the further heat exchange fluid is compressor bleed air bled from a core compressor of the gas turbine engine.

A fuel system for a hydrogen fueled gas turbine engine comprises a main hydrogen fuel storage unit configured to store liquid hydrogen. The main fuel storage unit comprises an ullage space configured to store ullage fluid comprising gaseous or supercritical hydrogen. The system further comprises a liquid hydrogen drain line configured to provide liquid hydrogen from the main hydrogen fuel storage unit to a fuel conduit, the fuel conduit being configured to supply hydrogen fuel to a combustor of the gas turbine engine. A priming line is provided, which is configured to provide ullage fluid to the fuel conduit, and a priming valve is configured to selectively control flow through the priming line.

The invention discloses a multi-dimensional multi-physics field coupling analysis platform of a hydrogen fuel cell based on artificial intelligence, and relates to the technical field of hydrogen fuel cells, the platform comprises a user interaction interface module, a multi-physics field model construction module, a data acquisition and preprocessing module, an integration module and an analysis and result output module; an electrochemical reaction model, a temperature field model and a gas and liquid flow model are respectively built through a multi-physical field model building module, the coupling strength among different physical fields is quantified, and the electrochemical reaction model, the temperature field model and the gas and liquid flow model are integrated into a multi-physical field model; physical action parameters such as electrochemical reaction rate, temperature value and the like are associated with time change, spatial distribution and fault conditions, so that the platform can simulate the multi-physical field coupling effect of the hydrogen fuel cell under complex working conditions, and the performance of the fuel cell is analyzed; and a reliable basis is provided for the geometric structure, material selection and operation condition optimization of the fuel cell.

The invention discloses a turbulent combustion characteristic prediction method, device, equipment and medium, and aims to rapidly and accurately predict hydrocarbon fuel turbulent combustion characteristics, the turbulent combustion characteristic prediction method comprises the following steps: constructing a three-step reaction mechanism, the three-step reaction mechanism comprises a first reaction mechanism using hydrocarbon fuel and oxygen as reaction fuels; a second reaction mechanism using carbon monoxide and oxygen as reaction fuels; a third reaction mechanism in which hydrogen and oxygen are used as reaction fuels; a three-step reaction mechanism is carried out by taking hydrocarbon fuel as fuel through a zero-dimensional isobaric flame model, the highest temperature during complete combustion of the hydrocarbon fuel is determined as adiabatic equilibrium temperature, and the maximum value point of the temperature change rate in the combustion process of the hydrocarbon fuel is determined as ignition delay; the laminar flame velocity is determined according to the index relationship between the reaction pressure and the laminar flame velocity through a three-step reaction mechanism by taking hydrocarbon fuel as fuel through a one-dimensional isobaric flame model.

The embodiment of the invention discloses a nozzle suitable for a pure hydrogen gas turbine. According to one specific embodiment, the nozzle comprises a nozzle body, a first micro-mixing assembly, a second micro-mixing assembly, an air circulation annular piece, a first hydrogen fuel pipe and a second hydrogen fuel pipe assembly. The second hydrogen fuel pipe assembly comprises at least one second hydrogen fuel pipe, and the first hydrogen fuel pipe and the second hydrogen fuel pipes are arranged on the nozzle body. The nozzle body comprises a fuel chamber, and the air circulation annular piece is arranged in the fuel chamber. The micro-mixing pipes included in the first micro-mixing assembly are annularly and obliquely arranged layer by layer around the first hydrogen fuel pipe, the micro-mixing pipes included in the second micro-mixing assembly are annularly and obliquely arranged layer by layer around the air circulation annular piece, and the micro-mixing pipe inclination directions and the micro-mixing pipe inclination angles of the micro-mixing pipes in each micro-mixing pipe set are the same. According to the embodiment, the safety and the service life of the pure hydrogen gas turbine can be improved.

The invention relates to membrane electrode production equipment, and belongs to the technical field of hydrogen fuel cells. The invention provides membrane electrode production equipment, which comprises an upper frame unwinding module, a lower frame unwinding module and a membrane electrode production module, the CCM cutting and transferring module is used for providing a CCM sheet material; the lower frame cutting and transferring module is used for providing a lower frame semi-cutting and transferring material belt; the thermal compounding module is used for receiving the upper frame material belt, the CCM sheet material and the lower frame half-cut transfer material belt and performing hot pressing to form a composite material belt; the finished product cutting and stripping module comprises a finished product cutting mechanism and a finished product stripping mechanism, and the finished product cutting mechanism is used for carrying out half cutting on the composite material belt to form a half-cut MEA material belt; and the finished product stripping mechanism is used for stripping the MEA sheet material from the half-cut MEA material belt and outputting the MEA sheet material. According to the membrane electrode production equipment, the membrane electrode can be automatically produced, and the qualified rate of finished products and the quality control precision are relatively high.

The invention discloses a sleeve type annular cathode open type air cooling hydrogen fuel cell, and belongs to the technical field of hydrogen fuel cells. The air cooling module is vertically arranged on the rack, and the air cooling module comprises an inner cooling bin and an outer cooling bin coaxially arranged outside the inner cooling bin; an air cavity for conduction of an air source is defined between the inner cooling bin and the outer cooling bin; the hydrogen fuel cell stack is vertically arranged in the inner cooling bin; the inner cooling bin is a hollow rectangular shell with two open ends, and a through hole through which an air source is conducted to the hydrogen fuel cell stack is formed in the side wall in a penetrating manner; the outer cooling bin is a hollow rectangular shell with two open ends; the air suction module is vertically arranged in the middle of the inner cooling bin; and the air supply module is vertically arranged in the air cavity in a sliding mode, and the air supply module comprises an upper limiting unit and a lower limiting unit which are arranged in the air cavity in a sliding mode. According to the invention, efficient heat dissipation can be carried out on the hydrogen fuel cell stack, the heat dissipation section can be dynamically adjusted, and the heat dissipation efficiency is high.

Disclosed is a marine fuel cell-based integrated heat, electricity, and cooling supply system comprising a power supply system and a waste heat recovery system; the power supply system comprises wind turbine generator sets, solar generator sets, and a fuel cell power module; the waste heat recovery system encompasses a turbine power generation module and a lithium bromide refrigeration module; the fuel cell power module is connected to both the turbine power generation module and the lithium bromide refrigeration module; the turbine power generation module is used to generate electricity using waste heat. This approach fully exploits the waste heat from the exhaust gas generated by the fuel cell power module, resulting in a high overall energy utilization rate. The self-consumption electricity and pure hydrogen fuel for the integrated energy supply system can be obtained from solar and wind energy, ensuring low carbon emissions for the entire system.

The invention provides an aerial photovoltaic system and a high-efficiency energy management method thereof, and the system comprises a self-adaptive floating platform, a high-efficiency light photovoltaic module, a linear energy transmission system and an intelligent attitude regulation and control and flight control system, and is based on an AI meteorological data prediction algorithm and in combination with a GPS / Beidou positioning module. A servo motor, a telescopic cable and an electric propulsion fan are driven to adjust the orientation of the photovoltaic panel and the height of the platform; according to the energy storage and management system, a solid-state lithium battery and a hydrogen fuel battery are combined, electric energy distribution is optimized, and dynamic balance of photovoltaic power generation, energy storage and wireless transmission is achieved. Through dynamic adjustment of the suspension height, intelligent illumination tracking and efficient wireless power transmission, the problems that traditional ground photovoltaic land occupation is limited and transmission loss is high are solved, light weight, wind resistance stability and day and night power supply capacity are achieved, and the power generation efficiency and environmental adaptability are greatly improved.

The invention belongs to the technical field of aviation electric propulsion, and relates to a hydrogen fuel cell superconducting hybrid electric propulsion system based on hydrogen and helium heat exchange cooling, which is suitable for megawatt level branch aircrafts and comprises a liquid hydrogen storage tank, a hydrogen and helium heat exchanger, a hydrogen fuel cell, a lithium battery, an inverter, a superconducting motor, a propeller and other core components. The liquid hydrogen storage tank vaporizes liquid hydrogen through the micro-channel plate type hydrogen-helium heat exchanger and stably supplies the vaporized liquid hydrogen to the hydrogen fuel cell to generate electric energy; helium is used for a low-temperature cooling loop and cooling key assemblies such as a superconducting motor, a low-temperature inverter, a superconducting cable and a hydrogen fuel cell, and it is ensured that the key assemblies stably operate at the optimal working temperature. The hydrogen fuel cell and the lithium battery cooperatively provide electric energy for the superconducting electric propulsion system, the integrated energy management controller dynamically adjusts the output power of the fuel cell and the lithium battery by adopting a state machine strategy, and accurate monitoring and optimal distribution of working parameters of all components are achieved. The optimal heat balance and power output are ensured to be realized in different flight stages such as takeoff, cruise and landing; according to the hydrogen fuel cell hybrid electric propulsion system based on hydrogen and helium heat exchange cooling, the power generation efficiency and the operation stability of the hydrogen fuel cell are remarkably improved, the overall energy conversion efficiency is improved, and the high-power and high-efficiency power extraction requirements of megawatt aircrafts are fully met.

The invention relates to the technical field of hydrogen fuel cells, in particular to a porous channel heat dissipation structure matched with a bipolar plate of a hydrogen fuel cell, the porous channel heat dissipation structure comprises a sealing outer frame and a bipolar plate body, the interior of the sealing outer frame is fixedly connected with the outer wall of the bipolar plate body, the bipolar plate body comprises an anode single plate and a cathode single plate, a working gas inlet hole is formed in the outer wall of the top of the bipolar plate body; the cooling device has the beneficial effects that uniform mixing of ethylene glycol and the cooling liquid is further improved by stirring the cooling liquid, meanwhile, the flowing speed and turbulivity of the cooling liquid can be increased by stirring the cooling liquid, heat can be taken away more quickly by the cooling liquid, slow flowing of the cooling liquid in the cooling tank is avoided, and the cooling effect is improved. Correspondingly, the flow velocity of the cooling liquid is increased through the arrangement of the rotating blades, so that the effect that the cooling liquid drives heat on the bipolar plate body is improved, and bubbles generated by ethylene glycol can be broken through the shearing acting force of the rotating blades and are converted into smaller bubbles.

The invention discloses a hydrogen fuel cell unmanned aerial vehicle energy management and trajectory tracking cooperative control method, and belongs to the field of hydrogen fuel cell long-endurance unmanned aerial vehicle energy management and trajectory tracking control. According to the method, the influence of external disturbance and model uncertainty is studied, fixed time control and active disturbance rejection control principles are introduced, a double-closed-loop unmanned aerial vehicle trajectory tracking method based on fixed time active disturbance rejection control is designed, and effective unmanned aerial vehicle working condition demand information and power control output in a time domain are obtained; based on demand information generated by trajectory tracking control, factors such as hydrogen fuel cell temperature difference, lithium battery SoC maintenance, hydrogen fuel consumption and energy source service life are comprehensively considered, a life attenuation cost function and an energy consumption cost function based on minimum equivalent fuel consumption are established, and an intelligent energy management cooperative control method fusing trajectory tracking control is designed. Hydrogen consumption is reduced, and the cruising ability of the whole machine is improved.