1827results about "Transportation hydrogen technology" patented technology

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 battery heating device includes: a radiator and a heater core arranged in parallel with each other; a battery temperature adjusting unit for heating a battery with a heat medium; a first branch branching the heat medium between the radiator and the heater core; a first confluence where the heat medium merges; a second branch where the heat medium from a heat emitter is branched to the battery temperature adjustment unit; a second confluence where the heat medium flowing through the battery temperature adjustment unit merges; and a radiator flow rate reducing part arranged in a passage for the heat medium from the first branch or the second branch closer to the radiator to the first confluence or the second confluence closer to the radiator via the radiator.

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.

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 unmanned aerial vehicle hydrogen-electricity hybrid power system comprises a vehicle body, a hydrogen fuel cell system, a power cell system and an energy management system are arranged in the vehicle body, and electric energy output by the hydrogen fuel cell system and the power cell system supplies power to a motor through the energy management system; the motor controls the spiral blades, the rotating speed of the motor is independently adjusted, and the posture and movement of the unmanned aerial vehicle are controlled by changing the direction and size of the lifting force; the energy management system is used for performing energy conversion during air speed change and braking of the unmanned aerial vehicle, converting mechanical energy into electric energy, inputting the electric energy into the power battery system, and meanwhile, converting the electric energy to judge whether the unmanned aerial vehicle has a high-power energy supply demand currently so as to adjust energy supply; according to the invention, the service life of the galvanic pile monomers can be prolonged, so that the service life of the hydrogen-electricity hybrid power system module can be prolonged; according to the energy management method, unnecessary energy loss is reduced, and the endurance time of the unmanned aerial vehicle is further prolonged.

The invention discloses an unmanned aerial vehicle hybrid power supply system energy management method based on fuzzy double closed-loop control in the technical field. An unmanned aerial vehicle hybrid power supply system comprises a hydrogen fuel cell, a lithium battery and a double active bridge circuit, and the hydrogen fuel cell and the lithium battery serve as energy sources of the hybrid power supply system; the dual-active bridge circuit is used for connecting a hydrogen fuel cell and a lithium battery and transmitting energy to an unmanned aerial vehicle load, the energy management method comprises a fuzzy power control outer ring and a fuzzy PI current control inner ring, the fuzzy power control outer ring dynamically distributes power according to a power signal required by the unmanned aerial vehicle load, a power error signal and a lithium battery charge state, and the fuzzy PI current control inner ring controls the power to be output. The fuzzy PI current control inner loop generates an accurate driving signal according to the battery power and the voltage ratio after fuzzy distribution, a switching device of the dual active bridge circuit is driven to be switched on, energy transmission is achieved, and the problems that in existing unmanned aerial vehicle energy management, the cruising ability is insufficient, and the energy utilization efficiency is low can be effectively solved.

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 work vehicle includes a fuel cell power generation system, an inverter connected to the fuel cell power generation system, a motor connected to the inverter, and a vehicle frame supporting the fuel cell power generation system, the inverter, and the motor, the vehicle frame rotatably supporting left and right front wheels and left and right rear wheels. The vehicle frame includes a transmission case housing a transmission to transmit driving force from the motor to the rear wheels. The inverter is at a side of the transmission case.

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 work vehicle includes a fuel cell module including a fuel cell stack, at least one fuel tank to store fuel to be supplied to the fuel cell stack, a sensor to measure a remaining amount of fuel in the at least one fuel tank, a motor connected to the fuel cell module, a power take-off shaft driven by the motor and to which an implement is connected, a display, and a processor configured or programmed to estimate, based on the measured remaining amount of fuel and a type of the implement connected to the power take-off shaft and / or a type of work performed by the implement, at least one of a travelable distance, a travelable area, or a travelable time with the work, and to display an estimation result on the display.

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 present invention discloses a fuel cell throttle, which includes a throttle body, an inlet and outlet arranged on both sides of the throttle body, and two closed valves arranged in the throttle body, the two closed valves are arranged opposite to each other up and down, and the two closed valves are respectively connected with elastic reset parts; the fuel cell throttle also includes a driving mechanism for driving the two closed valves to open, and the output execution end of the driving mechanism can be connected to the two closed valves in a transmission manner. The fuel cell throttle proposed in the embodiment of the present invention can open the upper and lower closed valves by air pressure when the driving mechanism loses power or fails, so that air flows from the throttle inlet to the throttle outlet, thereby avoiding damage to the battery stack due to excessive pressure. In addition, the present invention also proposes a fuel cell system and a fuel cell vehicle.

A work vehicle includes a fuel cell, at least one fuel tank to store fuel to be supplied to the fuel cell, a motor connected to the fuel cell, a vehicle frame supporting the fuel cell, the fuel tank, and the motor, the vehicle frame rotatably supporting front and rear wheels, at least one enclosure housing the fuel cell and the fuel tank, and at least one fuel gas sensor inside the enclosure.

An aircraft, such as a rotorcraft, may have at least one area designated to house at least one fuel cell and at least one aircraft structure that may translate, during a drop impact of the aircraft, into the area designated to house the fuel cell. At least one shaped fuel cell may be provided and deployed therein, in accordance with the present systems and methods. Each respective shaped fuel cell may define at least one respective through-voids defined through the respective shaped fuel cell, and / or at least one respective edge cavity defined along an edge of the shaped fuel cell, wherein the respective through-void and / or the respective edge cavity correspond to the respective aircraft structure that may translate, during the drop impact of the aircraft, into the area of the aircraft designated to house the respective fuel cell to receive and accommodate the respective structure during the drop impact.

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.

A cooling system for a fuel-cell system onboard a vehicle such as an aircraft in one embodiment employs the latent heat of evaporation of a two-phase coolant to reduce mass and parasitic power requirements of the cooling system. In another embodiment the cooling system has a primary ambient air heat exchanger coolant loop for cooling the fuel-cell system, and a secondary coolant loop comprising a fluid circuit configured to circulate a coolant in thermal contact with a phase-change material (PCM) in thermal contact with the fuel-cell to absorb heat from the fuel-cell. The secondary coolant loop includes a heat pump for cooling the PCM.

The invention discloses a hydrogen energy endurance supply regulation and control management system and method suitable for a hydrogen energy unmanned aerial vehicle, and belongs to the technical field of energy supply regulation and control. The method comprises the following steps: constructing a theoretical endurance mileage model, and calculating the theoretical endurance mileage which can be reached by the unmanned aerial vehicle in an ideal state after one hydrogen storage bottle is used up; collecting flight data of the unmanned aerial vehicle, inputting the flight data into a pre-trained artificial intelligence algorithm model, obtaining the endurance loss amount of the unmanned aerial vehicle in the current flight state, and further obtaining a first endurance mileage; a flight attitude combination used by the unmanned aerial vehicle in the flight process is obtained, and the predicted endurance mileage is calculated; based on the predicted endurance mileage of the unmanned aerial vehicle needing hydrogenation and the hydrogen capacity and the hydrogen concentration of the current remaining hydrogen storage cylinders, the unmanned aerial vehicle matched with the hydrogen concentration of the remaining hydrogen storage cylinders is screened out, and the hydrogen concentration of the hydrogen storage cylinders is preferentially distributed to the matched unmanned aerial vehicle; in the hydrogenation process, the required hydrogen energy capacity and the corresponding hydrogen concentration are calculated.

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.

An agricultural work vehicle includes a fuel cell power generation system, a first voltage conversion circuit to convert a voltage output from the fuel cell power generation system to output a first voltage, and a second voltage conversion circuit to convert the voltage output from the fuel cell power generation system to output a second voltage higher than the first voltage.

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 method of driving a fuel cell-based vehicle may include determining whether the vehicle is in an ignition entry state, determining an open-circuit voltage of a battery that provides a voltage to the air compressor based on the vehicle being in the ignition entry state, determining a drive current provided to the air compressor from the battery based on the open-circuit voltage, and driving the air compressor based on the drive current.

An aircraft hybrid motive power source system includes: a gas turbine engine mounted on an aircraft and including a low-pressure shaft and a high-pressure shaft as rotary shafts; a first motor generator drivingly connected to the high-pressure shaft; a second motor generator drivingly connected to the low-pressure shaft; a fuel cell to which a fuel gas and an oxidant gas are supplied; a fuel gas generator configured to generate the fuel gas from a raw material by heating using an exhaust gas from the gas turbine engine; and a controller configured to supply an electric power of the fuel cell obtained by a supply of the fuel gas to one of the first motor generator and the second motor generator, based on at least one of information indicating an operating status of the gas turbine engine and an electric power demand of the aircraft.

The present disclosure provides systems and methods for storing, transporting, and using hydrogen. In some embodiments, the method may comprise (a) storing hydrogen fuel in one or more fuel storage modules; (b) transporting the one or more fuel storage modules to a vehicle fueling site, wherein one or more hydrogen fuel compatible vehicles are located at or near the vehicle fueling site; (c) loading the one or more fuel storage modules into the one or more hydrogen fuel compatible vehicles, wherein the one or more fuel storage modules are configured to be releasably coupled to the one or more hydrogen fuel compatible vehicles; and (d) decoupling the one or more fuel storage modules from the one or more hydrogen fuel compatible vehicles after the one or more fuel storage modules are depleted or partially depleted.

An aircraft propulsion module comprises a hydrogen storage system, an electrochemical converter (7) connected to the hydrogen storage system, wherein the at least one electrochemical converter is adapted to convert hydrogen supplied from the hydrogen storage system (12) into electric energy, and an electric motor (5) electrically connected to the electrochemical converter, wherein the electric motor is adapted to generate thrust; wherein the propulsion module comprises at least one separation means (9) adapted to separate at least one component of the propulsion module from the propulsion module. An aircraft comprises at least one such aircraft propulsion module. A method for operating a propulsion module comprises that: during operation of the propulsion module, at least one separation means is actuated, by which actuation at least one component of the propulsion module is separated from the remaining propulsion module and then falls from the remaining propulsion module.

A work vehicle includes a fuel cell module including a fuel cell stack, at least one fuel tank to store fuel to be supplied to the fuel cell stack, a motor connected to the fuel cell module, a power take-off shaft drivable by the motor and to which an implement is connectable, and a controller configured or programmed to be operable in various control modes including a normal mode and an output limitation mode in which an upper limit value of electric power supplied from the fuel cell module to the motor is smaller than in the normal mode. In the output limitation mode, the controller is configured or programmed to alter the upper limit value of the electric power supplied to the motor according to at least one of a type of the implement connected to the power take-off shaft and a type of work performed by the implement.

A synchronous high voltage control system for a fuel cell battery electric vehicle (FCBEV) includes a fuel cell propulsion system (FCPS) configured to control a fuel cell system of an electrified powertrain of the FCBEV based on a mode control signal, wherein FCPS is configured to control the fuel cell to selectively support a high voltage bus, and an electrified vehicle control unit (EVCU) configured to (i) supervise a battery pack control module (BPCM) that is configured to control contactors to connect or disconnect a high voltage battery system to and from the high voltage bus and (ii) generate the mode control signal for the FCPS, wherein the EVCU is configured to utilize the mode control signal to have synchronous behavior across all high voltage systems of the FCBEV including the high voltage battery system and the fuel cell system.