1321results about "Transportation hydrogen technology" patented technology

An aircraft propulsion assembly that has a nacelle with a front opening and a rear opening, a propeller driven by an electric motor, a fuel cell supplying the electric motor with electric current, an inner channel arranged in the nacelle between the front opening and the rear opening. The electric motor and the fuel cell are disposed in the inner channel. A motorized fan is arranged at the rear part so as to draw in the air present in the inner channel and expel it to the outside through the rear opening. A control unit controls the motorized fan. With such an arrangement, the outside air cools the inside of the nacelle and the dihydrogen is evacuated.

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 invention discloses a hydrogen fuel cell ship power switching system, which relates to the technical field of hydrogen fuel cell ship hybrid power, and comprises a topological optimization module for optimizing a series-parallel topological structure of a fuel cell stack through a quantum annealing algorithm based on a multi-modal data set, the reconfigurable bipolar plate magnetic control switch is triggered to execute millisecond topology switching, and a topology state coding signal is synchronously generated; and the compensation module is used for inputting the topological state coding signal into the LSTM model, predicting a fault risk value, correcting the time step length of a leakage diffusion equation according to the real-time switching frequency of a magnetic control switch, and calculating a ship inclination angle correction term according to the corrected time step length. According to the invention, through an accurate fault prediction and compensation mechanism, operation interruption and maintenance cost caused by unpredictable faults are greatly reduced.

The invention belongs to the technical field of aircraft design, and particularly relates to an integrated tilting power system integrated with hydrogen fuel cell motor electric control and an aircraft. Comprising a tilting mechanism connected with a machine body; the integrated motor and controller is fixedly connected with the tilting mechanism and located at the end, close to the upstream of the incoming flow, of the tilting mechanism; the tilting rotor wing is mounted at one end, close to the incoming flow upstream, of the integrated motor and controller; the hydrogen fuel cell is fixedly connected with the tilting mechanism and is positioned at one end, close to the downstream of the incoming flow, of the tilting mechanism; the nacelle shell wraps the tilting mechanism, the integrated motor, the controller and the hydrogen fuel cell; the nacelle outer heat dissipation fins wrap the nacelle in the circumferential direction; and the tilting mechanism, the integrated motor and controller and the liquid cooling radiating pipeline of the hydrogen fuel cell exchange heat with the radiating fins outside the nacelle.

A hydrogen aircraft includes: an airframe including a fuselage and a wing; at least one propulsion system fixed to the airframe; a pressurized chamber disposed inside the fuselage; a pressure bulkhead that is disposed at a rear part of the pressurized chamber and has strength to withstand pressurization of the pressurized chamber; a hydrogen tank that is disposed in an accommodation section and stores liquid hydrogen, the accommodation section being installed behind the pressure bulkhead, outside the pressurized chamber, and inside the fuselage; and a supply line that supplies the liquid hydrogen stored in the hydrogen tank to the propulsion system.

A method and control system for a fuel cell system for a fuel cell vehicle comprising the fuel cell system comprising at least one fuel cell stack, and a cooling system. Processing circuitry of the control system may be configured to, for each fuel cell system power output in a plurality of fuel cell system power outputs, determine a cooling electrical power value indicative of cooling electrical power required to be supplied by the fuel cell system to the cooling system for rejecting output heat generated at least by the fuel cell system, determine a net electric power output value indicative of net electric power output that can be supplied from the fuel cell system to one or more electric power consumers when operating to produce the fuel cell system power output, and using the net electric power output value for determining a fuel cell system output level threshold for the fuel cell system.

An electric vehicle (EV) battery unit and installation method is provided herein. The EV battery unit includes a modular housing with a central section with batteries positioned therein and a first lateral section with a battery cooler that is designed to reduce a temperature of the batteries and an inverter that is positioned therein and electrically coupled to the batteries. The modular housing further includes a first frame attachment interface profiled to attach to a first longitudinal frame rail in an EV and a second frame attachment interface profiled to attach to a second longitudinal frame rail in the EV, where the batteries are positioned laterally between the first and second frame attachment interfaces.

The subject matter described herein generally relates to look ahead energy management and control systems and methods for detecting, incorporating, and leveraging look ahead technology data to improve the performance, durability, and life of fuel cell systems.

An arrangement for a vehicle includes a fuel cell, an electric traction and / or propulsion motor, and a single cooling circuit cooling the fuel cell and the electric motor. The cooling circuit includes two parts: a first, high-flowrate and high-temperature part including a high-temperature exchanger and a second, low-flowrate and low-temperature part including a low-temperature exchanger. The first part cools the fuel cell and the second part cools the electric motor. The first part includes a high-flowrate pump, in particular for a high flowrate of between 8000 l / h and 9000 l / h and the second part includes a low-flowrate pump, in particular for a low flowrate of between 2000 l / h and 3000 l / h.

The invention relates to a thermal management system of a hydrogen fuel cell hybrid power vehicle. The thermal management system comprises a fuel cell cooling system and a fuel cell thermal utilization system. The fuel cell cooling system is connected with the fuel cell heat utilization system through a heat exchanger; the turbine power generation unit is used for generating electric energy by using heat of the fuel cell cooling system; and the warm air units are arranged in the driver cabin and the passenger cabin and are used for heating by utilizing the heat of the fuel cell cooling system. The fuel cell cooling system and the fuel cell heat utilization system are connected through the heat exchanger, the warm air unit and the turbine power generation unit are arranged in the fuel cell heat utilization system, different working modes are selected according to different working environments, when heating is needed, waste heat of the fuel cell system is fully utilized for heating, and the energy consumption is reduced. When heating is not needed, waste heat is converted into electric energy to be stored through the turbine generator, and the energy efficiency of the fuel cell system is effectively improved.

A silencer for a fuel cell vehicle includes: an internal pipe including a first drain disposed in a lower portion of an external circumferential surface thereof and configured to discharge water and a plurality of gas flow ports disposed in an upper portion of the external circumferential surface and configured to allow gas to flow therethrough; a housing surrounding the internal pipe and forming a space in which the water and the gas flow within the internal pipe; a drainage adjustment portion disposed inside the internal pipe and configured to open or close the first drain, wherein the drainage adjustment portion includes: a moving plate including a shape corresponding to a cross section of an internal space of the internal pipe and moving in an axial direction of the internal pipe according to flow of the gas.

The present invention discloses a fuel cell engine, which comprises a fixed frame. The fixed frame includes a first side fixing plate, a second side fixing plate, a third side fixing plate and a fourth side fixing plate; a fuel cell, which includes a housing, an electric stack, a distributor, and a first end cap and a second end cap that are opposite in the third direction; a hydrogen supply system, which is installed on the first side fixing plate; a cooling circulation system, which is installed on the first side fixing plate; an air supply system, which is installed on the third side fixing plate; and a power distribution device, which is installed on the second side fixing plate. The fuel cell engine according to the embodiment of the present invention has the advantages of high integration, compact structure, high volume power density, small volume, easy assembly, high strength, good seismic resistance, etc.

A hydrogen tank includes a tank body, a boss connected to at least one end of the tank body and having a skirt extending radially with respect to an axial direction of the tank body, and a nozzle installed inside the tank body via the boss and configured to spray hydrogen gas at a predetermined angle with respect to the axial direction of the tank body. The nozzle includes a connector coupled to the boss, an extension portion extending from the connector parallel to the axial direction of the tank body, an inclined portion connected to an end portion of the extension portion and inclined with respect to the axial direction of the tank body, and an injection member provided at an end portion of the inclined portion.

The invention relates to the technical field of unmanned aerial vehicles, in particular to a hydrogen energy unmanned aerial vehicle and a control method thereof.According to the unmanned aerial vehicle, a hydrogen fuel cell serves as a power source, a hydrogen storage tank is arranged at the top of an inner cavity of an unmanned aerial vehicle body, the hydrogen fuel cell is arranged at the bottom of the inner cavity, and then long-time-efficiency driving of rotors is achieved; therefore, the unmanned aerial vehicle can meet the requirements of long-endurance and large-range task scenes, and a stable triangular supporting structure is formed through the unique layout of the three two-fork wing arms. Two brushless motors are installed at the tail end of each binary wing arm to form a power system with six rotors in total, the layout remarkably improves power redundancy, that is, when any rotor or even one rotor on a single binary wing arm breaks down, the other rotors can provide higher asymmetric torque compensation capacity, and by combining a specific control algorithm, the power redundancy can be greatly improved. The basic flight attitude and controllability of the unmanned aerial vehicle can be effectively maintained, and the flight safety and reliability are greatly improved.

A computer system (100) comprising processing circuitry (102) configured to: simulate a power output profile for an upcoming route (116) for a vehicle (104), acquire cooling efficiency information (114) of a cooling system (112, calculating the power output available from the fuel cell system (108) without overloading the cooling system (112), determine a control strategy (132) for energy stored in the electrical energy storage system (110) from a present position (P1) to the end of the route (116), execute the control strategy (132), and update the simulation and the control strategy while the vehicle (104) is travelling the route.

An apparatus comprises a power electronic energy conversion system comprising a first energy storage device configured to store DC energy and a first voltage converter configured to convert a second voltage from a remote power supply into a first charging voltage configured to charge the first energy storage device. The apparatus also includes a first controller configured to control the first voltage converter to convert the second voltage into the first charging voltage and to provide the first charging voltage to the first energy storage device during a charging mode of operation and communicate with a second controller located remotely from the power electronic energy conversion system to cause a second charging voltage to be provided to the first energy storage device during the charging mode of operation to rapidly charge the first energy storage device.

The invention relates to the technical field of unmanned aerial vehicles, and discloses a fuel cell unmanned aerial vehicle carrying double hydrogen cylinders, comprising: a hydrogen storage system comprising two independent gaseous hydrogen storage cylinders, the hydrogen storage system being connected with a fuel cell system through a hydrogen delivery pipeline to supply hydrogen to the fuel cell system; the fuel cell system is used for converting hydrogen into electric energy, and the fuel cell system is connected with the energy storage system through an electric energy transmission line so as to transmit the generated electric energy to the energy storage system; the control system is used for monitoring and regulating various functions of the unmanned aerial vehicle, and the control system is connected with the fuel cell system, the energy storage system and the power flight system through data transmission lines so as to receive and send control instructions. By adopting the double-gas-state hydrogen storage cylinder system, the unmanned aerial vehicle can carry more hydrogen, so that the flight endurance time and distance are prolonged, in addition, the hydrogen cylinders which are modularly designed are convenient to replace quickly, and continuous operation in a long-time task is further ensured.

A vehicle provided with a frame (1) comprising two side members (2, 3) connected together at least by a cross member (4), an alternative fuel module (6) and a support system (5) connected to the frame (1) for supporting the alternative fuel module (6), the support system (5) comprising at least a first support element (7) and a second support element (8), both being configured to be fixedly connected to the alternative fuel module (6) via coupling portion (11, 9b′), the coupling portion (9b′) of the second support element (8) being connected to both the side members (2, 3) and the coupling portion (11) of the first support element (7) being connected to the cross member (4) via a movable connection.

The invention discloses a fuel cell-turbofan engine hybrid power system for a cross-medium aircraft, and relates to the technical field of aero-engines, the system comprises a solid oxide fuel cell, a turbofan engine, a lithium battery, an energy management module, a motor, a propeller, a reforming hydrogen production device and a medium self-adaptive oxidant supply subsystem. In an air flight mode, the system adopts autothermal reforming hydrogen production, a fuel cell and a turbofan engine to cooperatively work, a high-efficiency low-oil-consumption low-speed cruise and high-thrust acceleration mode is provided, and meanwhile, a lithium battery is charged. In the underwater submerging and water surface sailing mode, a turbofan engine flow channel is closed, steam reforming hydrogen production is adopted, a hybrid power system composed of a fuel cell and a lithium battery is used for driving a propeller, the fuel cell provides stable power, and the lithium battery meets the instantaneous high-power requirement. The system solves the problems that a traditional power system is low in efficiency, poor in cruising ability, single in working mode and the like.

A propulsion system (100) for an aircraft as disclosed herein may include a nacelle (180), a shaft (110) positioned centrally within a cylindrical passageway (184) of the nacelle (110), a fan (120) coupled to one end (112) of the shaft (110), a turbine (130) coupled to an opposite end (114) of the shaft (110), an electric motor (140) coupled to the shaft (110), a compressor (160) positioned within the cylindrical passageway (184), and a solid oxide fuel cell (150) positioned with a hollow ring-shaped interior (182) of the nacelle (180). The hollow ring-shaped interior (182) may surround and be isolated from the cylindrical passageway (184). The turbine (130) may be configured to provide primary torque to the shaft (110) while the electric motor (140) may be configured to provide additional torque to the shaft (110). The electric motor (140) may be powered an electric output (152) of the solid oxide fuel cell (150) while the turbine (130) may be powered at least in part by output gases (154) from the solid oxide fuel cell (150).

A system for a blended wing body aircraft with a combustion engine is illustrated. The aircraft comprises a blended wing body, at least a fuel store located within the blended wing body and configured to store a fuel, wherein the fuel includes liquid hydrogen, and at least a propulsor 5 configured to propel the blended wing body aircraft. The at least a propulsor comprises a combustion engine configured to burn the fuel from the fuel store and produce mechanical work to power the at least a propulsor.

The invention discloses a heavy-load hydrogen-electricity hybrid power system of an industrial unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the core comprises a fuel cell, a lithium battery pack, a driving motor and three modules, the fuel cell and the lithium battery pack are connected in parallel with the driving motor, and a dynamic variable liquid cooling system is thermally connected with the fuel cell. The intelligent mission profile prediction module and the liquid cooling system are both in signal connection with the thermal-electric collaborative optimization controller, the prediction module receives data such as an air route and weather, simulates a flight state in a future time period through a model, and outputs predicted power and a temperature curve; the liquid cooling system comprises at least two independent heat dissipation partitions and is integrated with a paraffin-based composite phase change material, the optimization controller outputs optimal parameters through a task-adaptive multi-objective optimization function based on a prediction curve and real-time data, and the system is provided with a data acquisition module, a hydrogen supply control module and a fault early warning module to realize data monitoring, hydrogen supply stability and safety early warning. And the load, endurance and reliability are improved.

Hybrid propulsion systems that utilize liquid natural gas solid oxide fuel cells in a manner practical for use in aircraft that avoid the use of heavy batteries, provide transient response times suitable for use in aircraft, and / or simplify reactant pre-conditioning systems using a compressor and turbine pair operatively coupled to the solid oxide fuel cell. Such hybrid propulsion systems for an aircraft may include a liquid natural gas solid oxide fuel cell, a motor driven by electric power from the solid oxide fuel cell, a gearbox operatively coupled to the motor, and a turbofan engine configured to generate thrust for the aircraft. The turbofan engine may be configured to provide electric power and shaft power and may include a duct fan that is operatively coupled to the motor via the gearbox, with the duct fan being driven by mechanical power from the gearbox and by the motor.

A fuel treatment system for a hybrid gas-electric propulsion system using a hydrocarbon fuel includes a fuel pre-treatment unit, a recuperator including a first fuel passage and a second fuel passage where the first fuel passage is in fluid communication with a fuel outlet of the fuel pre-treatment unit. A partial oxidation reformer includes a heated fuel inlet and a reformed fuel outlet. The heated fuel inlet is in fluid communication with the fuel pre-treatment unit via the first fuel passage. A solid oxide fuel cell includes an anode inlet and an anode outlet. The anode inlet is in fluid communication with the reformed fuel outlet of the partial oxidation reformer, and the anode outlet is in fluid communication with the second fuel passage of the recuperator. A combustor is in fluid communication with the anode outlet via the second fuel passage.

The invention discloses a methanol / aviation kerosene dual-fuel chemical regenerative hybrid aero-engine, relates to the technical field of environment-friendly processing, and solves the problems that the electricity demand of turboshaft engine airborne equipment is increased and the carbon emission of the engine is too high. A core engine system comprises an aviation fuel storage tank, an air inlet channel, an air compressor, a combustion chamber, a turbine system, an exhaust nozzle and a rotor wing, wherein the aviation fuel storage tank is communicated with the combustion chamber; the air inlet channel, the air compressor and the combustion chamber communicate in sequence. One part of the methanol reforming product is introduced into a combustion chamber to be mixed with aviation fuel for combustion, and the other part of the methanol reforming product generates power through a fuel cell; the combustion chamber, the turbine system and the exhaust nozzle are communicated, and fuel gas generated by the combustion chamber is introduced into the turbine system to drive the turbine system; the turbine system drives the gas compressor and the rotor wing. The fuel cell is used for generating electricity to meet the electricity demand of airborne equipment, the shaft power on the engine main shaft is reduced, the engine output power is effectively improved, and the operation stability of a core engine system is improved.

A propulsion system for an aircraft as disclosed herein may include a nacelle, a shaft positioned centrally within a cylindrical passageway of the nacelle, a fan coupled to one end of the shaft, a turbine coupled to an opposite end of the shaft, an electric motor coupled to the shaft, a compressor positioned within the cylindrical passageway, and a solid oxide fuel cell positioned with a hollow ring-shaped interior of the nacelle. The hollow ring-shaped interior may surround and be isolated from the cylindrical passageway. The turbine may be configured to provide primary torque to the shaft while the electric motor may be configured to provide additional torque to the shaft. The electric motor may be powered an electric output of the solid oxide fuel cell while the turbine may be powered at least in part by output gases from the solid oxide fuel cell.

Ion exchanger (1) used in a cooling system (50) of a fuel cell system, comprising: a connecting pipe portion (2) having both end portions configured to be respectively connectable to a predetermined pipe of the cooling system, the connecting pipe portion having a first flow path (R1) allowing a coolant introduced from one side to flow therethrough to the other side; a housing portion (3) intended to communicate with the connecting pipe portion; and a storage body (4, 5) mounted on the housing portion, having a second flow path (R2) in which a part of the coolant introduced into the connecting pipe portion branches and flows out of the connecting pipe portion and flows into the connecting pipe portion again, and stores an ion exchange resin (18) in the second flow path, wherein: an installation state of the storage body (4, 5) with respect to the housing area (3) can be changed in a variety of ways; and a proportion of the coolant in the connecting pipe region (2) flowing to the second flow path (R2) can be changed by changing the installation state of the storage body (4, 5), in which the storage body has a part mounted to project to the inside of the connecting pipe portion (2), and an inlet channel through which the coolant from the connecting pipe portion is introduced into the second flow path (R2) at the projecting part, and an outlet channel through which the coolant from the second flow path is discharged to the connecting pipe portion, and the installation state of the storage body (4, 5) can be changed by rotating the storage body by a predetermined angle with respect to an installation direction of the storage body with respect to the housing area (3) as an axial center, further comprising a movable piece (25), one end of which is pivotally mounted so that it is rotatable, and the other end of which is a free end on the connecting pipe area-side end face (10) of the storage body (4, 5) which projects to the inside of the connecting pipe area (2), in which a free end side of the movable piece (25) changes between a state in which it is positioned further on the upstream side of the first flow path (R1) than a rotation axis side and a state in which it is positioned further on the downstream side of the first flow path than the rotation axis side by changing the installation state of the storage body (4, 5).

A propulsion system for an aircraft as disclosed herein may include a nacelle, a shaft positioned centrally within a cylindrical passageway of the nacelle, a fan coupled to one end of the shaft, a turbine coupled to an opposite end of the shaft, an electric motor coupled to the shaft, a compressor positioned within the cylindrical passageway, and a solid oxide fuel cell positioned with a hollow ring-shaped interior of the nacelle. The hollow ring-shaped interior may surround and be isolated from the cylindrical passageway. The turbine may be configured to provide primary torque to the shaft while the electric motor may be configured to provide additional torque to the shaft. The electric motor may be powered an electric output of the solid oxide fuel cell while the turbine may be powered at least in part by output gases from the solid oxide fuel cell.

A vehicle frame for a fuel cell includes a first frame, a second frame, and a support frame interconnecting the first frame and the second frame and provided with a fluid tank and a battery mounted thereon. The fluid tank includes a pair of fluid tanks on outer sides of the first frame and the second frame in a width direction, and the battery is disposed between the pair of fluid tanks.

The invention discloses a ship alcohol hydrogen electric drive power supply system. By integrating methanol reforming power generation, intelligent energy storage and digital management technologies, carbon emission is reduced by more than 30% while fuel cost is remarkably reduced by 45%-55%, millisecond-level response, 95% of system energy efficiency and full-process intelligent monitoring are achieved, the problems of high cost, high pollution and low efficiency of traditional diesel power generation are comprehensively solved, and the system is suitable for large-scale popularization and application. And meanwhile, stable operation in a low-temperature environment and off-grid power supply capability are realized, and remarkable breakthroughs are made in economic benefits, environmental protection performance and intelligent level.