112 results about "Hybrid propulsion" patented technology

The invention discloses an extended-range hybrid propulsion double-source dynamic coupling energy management method, which comprises the following steps: carrying out global physical modeling on a double-source power system and a flight scene, and establishing a double-source dynamic coupling model; designing a reinforcement learning physical constraint reward function, performing optimization training on each coefficient of the reward function by adopting a QMPSO algorithm, and outputting an optimized reward function coefficient; a qualified double-source dynamic coupling model is verified, and a power distribution coefficient is optimized; outputting the optimal power distribution coefficient of the battery and the range extender; the superiority of the dual-source power cooperative control strategy in the aspects of flight economy, operation stability and system life guarantee is verified through multi-dimensional comparative analysis of each performance index. Cooperative power distribution of the battery and the range extender is achieved through dynamic coupling modeling and reinforcement learning, the flight scene load requirement is met, the system energy efficiency is improved, and the service life of parts is prolonged.

The invention discloses an unmanned ship self-adaptive safety redundancy system for an inland river ultra-shallow water environment and a control method. The system is composed of four-stage closed-loop redundancy of sensing, decision making, execution and laws and regulations. A 0.1 m-stage shallow water three-dimensional map is constructed in real time by a dual-millimeter-wave radar and a high-frequency single-beam sounding sonar; the main and standby controllers process the quay wall effect, backflow and grounding nonlinear disturbance on line through a BLF-RBFNN fixed time convergence algorithm, and the upper bound of convergence time is 4.2 s and is irrelevant to the initial state; the variable-configuration double-pump jet-air cushion hybrid propulsion device adjusts the draft on line according to the water depth of 0.12-0.45 m, and is matched with the self-righting honeycomb composite ship body to automatically stop leakage and return within 60 seconds when the ship body is damaged; and when the ship-end double control fails, the ship-shore cloud collaborative digital twinborn body completes regulation-level minimum risk takeover within 10 seconds. Experiments prove that the path error is less than or equal to 0.08 m and the fault degradation success rate is 100% in a 0.15 m water tank and 0.35 m Yangtze River channel, and zero-grounding, zero-overturning and zero-regulation illegal sailing of the ultra-shallow water unmanned ship is realized.

The invention relates to the technical field of gas turbine devices, and particularly provides a gas turbine hybrid propulsion control method for response matching and energy management. The method generates a gas turbine power variation curve and a response delay trajectory of the electrical power output unit, and forms a sequence of response reverse evolution trajectories. A response lag trend is identified based on the sequence, a reverse dynamic traction instruction set is generated, and reverse torque cooperative intervention is triggered when the electric excitation frequency is abnormal. And constructing an accumulated energy curved surface through time integration, and identifying an energy level coupling critical region and generating a system control response path in combination with a dynamic margin sequence. In the path execution process, the system continuously identifies non-structural disturbance, constructs a disturbance factor combination vector, projects the disturbance factor combination vector to a power principal axis vector space and reconstructs a control path. And finally, integrating the multiple types of instruction sets into a polymorphic coupling stable control instruction set to realize stable cooperative control and smooth power transfer between the gas turbine and the electric power output unit.

An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide vertical propulsion of the aircraft and a respective electrical machine of a plurality of electrical machines, each respective electrical machine configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.

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.

The invention provides a variable circulation hybrid electric propulsion system applied to an unmanned aerial vehicle and a propulsion method of the variable circulation hybrid electric propulsion system, and belongs to the technical field of aircraft propulsion. The problems of insufficient power and endurance of the unmanned aerial vehicle are solved. The four liquid rocket engines are arranged around the unmanned aerial vehicle body through the vehicle arms; each rotor wing is correspondingly arranged above the liquid rocket engine; a motor and a pump are arranged in the liquid-propellant rocket engine, and the combustion chamber is located below a shell of the liquid-propellant rocket engine and connected with the spray pipe. A fuel cell in the unmanned aerial vehicle body is located at the upper end of the unmanned aerial vehicle body. An energy storage cell is embedded into the lower middle portion of the fuel cell. The energy management system is embedded into the middle-upper part of the fuel cell; and the oxygen tank is positioned at the lower end of the fuselage. The fuel cell is adopted to charge the energy storage cell, the energy storage cell drives the pump to stably convey fuel to the combustion chamber, the problem that a traditional liquid rocket engine depends on complex external energy when started for multiple times is effectively solved, and rapid and reliable repeated starting of the engine is achieved.

This invention discloses a fuel cell hybrid propulsion system and its power fluctuation-consumption synergistic optimization method. The system includes a fuel cell power generation unit, a lithium-ion battery unit, an electric drive unit, a sensing and data acquisition unit, and an energy management controller. Based on near-end strategy optimization, an intelligent agent is constructed with system state and operating condition information as input and power source power allocation commands as output. A reward function integrating total energy consumption penalty and power fluctuation penalty is designed to drive the intelligent agent to learn the optimal energy management strategy in a continuous action space. This invention can suppress frequent and drastic fluctuations in lithium-ion battery power, extend battery life, ensure system safety, and minimize overall hydrogen fuel consumption while meeting dynamic power demand and safety constraints. It achieves synergistic optimization of long-term operational economy and system output stability, enabling efficient, smooth, and long-life operation of the hybrid propulsion system in dynamic environments.

A method for operating a hybrid-electric propulsion system of an aircraft is provided. The hybrid-electric propulsion system includes a gas turbine engine having a high pressure system, a low pressure system, and an electric machine coupled to one of the high pressure system or low pressure system. The method includes receiving data indicative of an actual or anticipated in-flight shutdown of the gas turbine engine; and adding power to the gas turbine engine through the electric machine in response to receiving data indicative of the actual or anticipated in-flight shutdown of the gas turbine engine.

The application discloses a kind of dual-source dynamic coupling energy management methods of range-extender hybrid propulsion, comprising: the whole domain physical modeling of dual-source power system and flight scene is carried out, and dual-source dynamic coupling model is established;Design reinforcement learning physical constraint reward function, the optimization training of each coefficient of reward function is carried out using QMPSO algorithm, and the reward function coefficient after optimization is output;Verify the dual-source dynamic coupling model of qualified, and the power distribution coefficient is optimized;The optimal power distribution coefficient of battery and range-extender is output;Through multidimensional comparative analysis to each performance index, verify the superiority of dual-source power collaborative control strategy in flight economy, operating stability and system life guarantee aspect.The application realizes the collaborative power distribution of battery and range-extender by dynamic coupling modeling and reinforcement learning, adapts flight scene load demand, improves system energy efficiency and prolongs component life.

A propulsion assembly includes a first torque source coupled with a first shaft and a second torque source coupled with a second shaft. A coupler selectively couples the first and second torque sources. When the first and second torque sources are coupled via the coupler, in response to a command to decouple the first torque source, an unloading operation is performed to decrease the torque output provided by the first torque source to a threshold, and when reached, the first shaft is decoupled from the coupler. When the first torque source is coupled with the coupler but the second torque source is not, in response to a command to couple the second torque source, a speed matching operation is performed to increase the speed of the second shaft to match a speed of the first shaft, and when the speeds are matched, the second shaft is coupled to the coupler.

A method for retrofitting an installation of a type used for a hybrid propulsion system for LNG carriers, said method being based on the steps of retrofitting an LNG carrier boiler of the installation, retrofitting an existing exhaust gas outlet and integrating a new exhaust gas outlet, forming an opening in the combustion chamber of said LNG carrier boiler, introducing exhaust gas from a GTPG inside the formed opening and adding a second superheater inside the exhaust gas outlet between said GTPG and said LNG carrier boiler, integrating an auxiliary steam and water system and integrating an automatic changeover extraction system and connecting both systems to said hybrid propulsion installation.

A hybrid propulsion system for a vehicle includes an internal combustion engine (ICE), a fuel cell, a hydrogen storage tank, a battery pack, an electric drive motor and a controller. The ICE has a first output that drives a generator, the generator providing a first output voltage. The fuel cell has a second output providing a second output voltage. The hydrogen storage tank is configured to store hydrogen and selectively and alternatively supply the hydrogen to both of the ICE and the fuel cell. The battery pack selectively and alternatively receives the first and second output voltage to charge the battery pack. The controller receives vehicle inputs and determines operational set points of the ICE and the fuel cell representative of an amount of the first and second output voltage to direct to the battery pack based on operating conditions.

Electrical architecture for an aircraft with thermal / electrical hybrid propulsion, comprising, for each turbine engine: an aeroplane AC electrical network, at least one first electrical machine mechanically coupled to a high-pressure shaft of the turbine engine; at least one second electrical machine mechanically coupled to a low-pressure shaft of the turbine engine; a reversible AC / AC electrical energy conversion module; switch elements; and an electronic system for controlling the conversion module and the switch elements, configured to put the architecture: in at least one so-called “power distribution hybridisation” operating mode corresponding to a first configuration of the switch elements in which the at least one second machine is coupled to the aeroplane network and at least one first machine is coupled to the aeroplane network via the electrical energy conversion module.

The invention relates to a method for controlling a drive system (M) comprising a turbine engine (TM) coupled to an electric machine (MEL), an electronic control unit (20) for controlling the drive system, the electronic control unit being connected to a power converter (12), and a drive system for selectively driving the electric machine in an engine mode and a generator mode in accordance with a reference torque filtered in an adaptive manner in order to exclude an excitation frequency range of at least one torsional mode of the drive system in accordance with a stator phase voltage of a permanent magnet alternator driven by the turbine engine. The invention also relates to a corresponding drive system and to an aircraft comprising such a drive system.

The present application relates to the technical field of spacecraft propulsion system, and more particularly to a micro-newton hybrid mode propulsion system and method based on gas working substance. The system comprises a gas storage unit, a gas supply unit, a thruster unit and a propulsion system driving and control unit. The gas storage unit adopts symmetrically arranged high-pressure gas cylinders connected through high-pressure isolation valves, and in combination with the automatic balancing strategy of the control unit, effectively solves the problem of on-orbit centroid drift. The gas supply unit includes parallel cold gas propulsion branches and electric propulsion branches, and each branch adopts a mechanical pressure reducer to eliminate vibration and noise caused by electromagnetic valve action from the source, realizing super-static operation of the system. The propulsion system driving and control unit controls the micro-newton cold gas thruster and the micro-newton electric thruster to work alone or in cooperation according to the distribution strategy based on the thrust critical point, realizing the optimal comprehensive efficiency of high precision and high specific impulse in the full thrust range, and being suitable for ultra-high precision space scientific exploration missions.

The invention relates to a hydrogen-electricity energy turbine hybrid propulsion engine system, which relates to the technical field of engines, and is characterized in that a motor driven by a hydrogen fuel cell and a hydrogen fuel gas turbine engine are connected in parallel by using a gear transmission unit, and the gear transmission unit has three switchable transmission modes; the propulsion structure establishes a transmission relationship with the motor and a power turbine of the hydrogen fuel gas turbine engine at the same time through a first transmission mode; the propelling structure only establishes a transmission relation with the motor through the second transmission mode; the propulsion structure establishes a transmission relationship only with the power turbine of the hydrogen fuel gas turbine engine through a third transmission mode. At least one of the hydrogen fuel gas turbine engine and the hydrogen fuel cell can be selectively used, so that the response speed of the engine system is increased, and infrared characteristics and noise of the engine system are reduced.

The invention relates to a method for controlling a drive system (M) comprising a turbine engine (TM) coupled to an electric machine (MET), an electronic control unit (20) for controlling the drive system, the electronic control unit being connected to a power converter (12), and a driver for selectively driving the electric machine in an engine mode and a generator mode in accordance with a reference torque filtered in an adaptive manner in order to exclude an excitation frequency range of at least one torsional mode of the drive system in accordance with a stator phase current of the electric machine. The invention also relates to a corresponding drive system and to an aircraft comprising such a drive system.

The application provides a high-compact heat management type jet engine multi-mode split hybrid propulsion system. The propulsion system has a parallel double-shaft structure, shaft work of a horizontal shaft I is transmitted to a vertical shaft through a bevel gear set I, and the vertical shaft transmits the transmitted shaft work to a horizontal shaft II through a bevel gear set II. The horizontal shaft II rotates to drive a fan to work and generate propulsion work. Three groups of low-temperature proton exchange membrane fuel cell stacks are coaxially and parallelly arranged on the horizontal shaft I, and four electric motors are coaxially and serially arranged on the horizontal shaft II. The propulsion system has two different working modes. One is hybrid power propulsion, in which the clutch does not work, and the fan can be driven by the transmitted shaft work or by the electric motor. The other is pure electric propulsion, in which the clutch works, the vertical shaft is disconnected, and the horizontal shaft I outputs useless work. The fan can only be driven by the horizontal shaft II driven by the electric motor.

A propulsion assembly includes a first torque source coupled with a first shaft and a second torque source coupled with a second shaft. A coupler selectively couples the first and second torque sources. When the first and second torque sources are coupled via the coupler, in response to a command to decouple the first torque source, an unloading operation is performed to decrease the torque output provided by the first torque source to a threshold, and when reached, the first shaft is decoupled from the coupler. When the first torque source is coupled with the coupler but the second torque source is not, in response to a command to couple the second torque source, a speed matching operation is performed to increase the speed of the second shaft to match a speed of the first shaft, and when the speeds are matched, the second shaft is coupled to the coupler.

The application discloses a wing-leg hybrid propulsion underwater glider and a working method thereof. The glider comprises a glider body, a bidirectional flexible wing-leg hybrid propulsion device and a control panel. The bidirectional flexible wing-leg hybrid propulsion device comprises a wire mechanism driving part, a limiting block assembly, flexible wings, a driving control unit and a shell assembly. The wire mechanism driving part is installed inside the shell assembly. The limiting block assembly is arranged at the middle part outside the shell assembly. The flexible wings are arranged symmetrically on the opposite sides of the limiting block assembly and are connected with the limiting block assembly. The driving control unit comprises a driving servo motor installed in the cabin of the glider body. The motor shaft of the driving servo motor is connected with the shell assembly. The flexible wings are connected with the driving control unit. The underwater glider can realize various motion modes according to different tasks and operation requirements, such as seabed operation, floating, sinking, moving and hovering, so that the operation range, operation capacity, maneuverability and practicability are improved.

The name of the invention is hybrid turbofan engine and solid oxide fuel cell propulsion system and related methods. A hybrid propulsion system utilizes a liquid natural gas solid oxide fuel cell in a practical manner suitable for an aircraft that avoids the use of heavy batteries, provides transient response times suitable for use in an aircraft, and / or simplifies a reactant pre-processing system using a compressor and turbine operably coupled to the solid oxide fuel cell. Such a hybrid propulsion system for an aircraft can include a liquid natural gas solid oxide fuel cell, an electric motor driven by electrical power from the solid oxide fuel cell, a gearbox operably coupled to the electric motor, and a turbofan engine configured to produce thrust for the aircraft. The turbofan engine can be configured to provide electrical power and shaft power, and can include a ducted fan operably coupled to the electric motor by the gearbox, the ducted fan driven by mechanical power from the gearbox and the electric motor.

The application provides a compact high-temperature fuel cell jet engine multi-mode split hybrid propulsion system, which is beneficial to solve the problems of low thermal efficiency, high fuel consumption and high nitrogen oxide emission of traditional aviation gas turbine engines. The system comprises a propulsion system, a transmission system and a lubrication system; the propulsion system adopts parallel double shafts; the two connecting shafts can transmit power through the transmission system to realize two working modes of the ducted fan; the lubrication system sends lubricating oil to all shafts on the shaft. The high-temperature solid oxide fuel cell system is used to supply power to the motor through the direct current conversion device, and then the motor drives the ducted fan, so that the total efficiency and total thrust of the hybrid propulsion system are improved. The hydrogen-rich combustion chamber and the hydrogen-lean combustion chamber are added to the structure, so that the problem of fuel preheating of the high-temperature solid oxide fuel cell through the heat exchanger with complex pipelines is solved.

A method for regulating the speed of a propulsion device of an aircraft including: the propulsion device and a gearbox MGB; the heat engine and at least one electric motor, mounted in parallel on the MGB, the heat engine having a fuel circuit; main and backup regulation systems, and a regulation system, each capable of regulating the speed of the heat engine or the electric motor, respectively; a control system of the aircraft, capable of sending a speed or power setpoint to each of the regulation of the heat engine and the electric motor. The method includes: sending a speed setpoint NM2ref to the regulation system of the electric motor, the regulation system sending a power command PM2*, to obtain an instantaneous power PM2m; simultaneously, sending a speed or power command to the backup regulation system of the heat engine, the backup regulation system sending a selected fuel flow command QCarbAux* to the fuel circuit of the heat engine.

The application provides a ship hybrid power propulsion system management method. The ship hybrid power propulsion system comprises a generator set and a lithium battery pack for supplying power to a load and storing electric energy, and the method comprises: acquiring system regulation information, the system regulation information comprising at least one of the residual capacity of the lithium battery pack, the load power and the number of generator sets; if it is determined that the system regulation information meets a preset condition, adjusting the working state of the system according to the met preset condition, the working state comprising at least one of the charging and discharging of the lithium battery pack, the increase and decrease of the generator set and the unloading of the load. The application can automatically adjust the working state of the lithium battery pack, the increase and decrease of the generator set and the like according to the system regulation information, effectively avoid the occurrence of system failure, reduce the operation cost and maintenance cost, fully exert the advantages of the hybrid power system, improve the energy utilization efficiency and the adaptability to various working conditions of the ship.

A hybrid propulsion system for a vehicle includes a battery for storing electrical energy, a power controller designed to direct electrical energy to and from the battery, a hybrid transaxle positioned between and connecting a power engine and a first drive axle, the hybrid transaxle comprising a planetary gear set including a sun gear, planet gears rotatably mounted on a carrier, and a ring gear, the carrier being permanently connected to the power engine, a first electric motor / electric generator permanently connected to the sun gear of the planetary gear set, final drive gears permanently connected to the ring gear of the planetary gear set and connecting it to the first drive axle, and a second electric motor / electric generator that can be selectively connected to the final drive gears via an intermediate gear set with a single gear ratio.

A hybrid propulsion installation for an aircraft, including an internal combustion engine having at least one combustion chamber; at least one electricity generator; an electrical propulsion system; electromechanical protection mechanism arranged between the or each electricity generator and the electrical propulsion system; wherein the installation also includes: an electronic computer configured to: receive at least one piece of information on a position of the electromechanical protection mechanism; receive at least one piece of information on a speed of rotation of a shaft of the internal combustion engine; and control the flow of fuel supplying the combustion chamber depending on the information received.

This utility model relates to the field of satellite propulsion equipment technology, and specifically provides an integrated gas-fuel hybrid propulsion system, including an integrated tank, gas generator, gas container, and thruster. The tank contains a flexible metal diaphragm, with one side forming a gas chamber and the other a liquid chamber. The gas chamber has a gas inlet, and the liquid chamber has a liquid inlet. The liquid inlet's output pipe is connected to the gas generator, the gas generator's output pipe is connected to the gas container, and the gas container's output pipe is connected to the thruster. This utility model solves the problems of low specific impulse in cold gas propulsion systems, heavy thruster mass and large envelope size in monocomponent chemical propulsion systems, and the difficulty in achieving low thrust output in bicomponent chemical propulsion systems, thus meeting the application requirements of satellites.

A method includes determining an operating mode of a hybrid electric propulsion system. The hybrid electric propulsion system includes a conditionally regulated high voltage direct current (HVDC) architecture. The conditionally regulated HVDC architecture includes a first switchable circuit formed between an HVDC bus, an HVDC electrical source, and a bi-directional direct current to direct current (DC-DC) converter configured to regulate electrical power flowing between the HVDC bus and the HVDC electrical source. The conditionally regulated HVDC architecture also includes a second switchable circuit formed between the HVDC bus and the HVDC electrical source. The method also includes configuring the conditionally regulated HVDC architecture based on the determined operating mode.

The utility model discloses a hybrid propulsion system of a methanol filling ship, which comprises three first dual-fuel generators, a second dual-fuel generator, four sets of lithium battery packs, a solar photovoltaic panel, a controller and an electric equipment group, the three first dual-fuel generators and the second dual-fuel generator are arranged in parallel and are electrically connected with the controller respectively; the four sets of lithium battery packs, the solar photovoltaic panel and the plurality of electric equipment are electrically connected with the controller; the electric equipment group comprises a side thrust motor, at least one main propulsion motor, at least one cargo oil pump and at least one marine daily power supply which are electrically connected with the controller respectively; the three first dual-fuel generators and the second dual-fuel generator can adopt methanol as fuel, the power of the first dual-fuel generators is larger than that of the second dual-fuel generator, the mode that diesel oil is adopted as driving fuel in the past is replaced, and the problems that energy consumption is high and environmental protection performance is insufficient in the past are solved.