287 results about "Hybrid propulsion" patented technology

A craft comprises at least one hull, a main wing coupled to the hull and configured to facilitate airborne operations of the craft, a plurality of propellers that include one or more electric motor propellers and one or more combustion motor propellers arranged along each of a port side and a starboard side of the main wing and configured to generate lift on the craft by blowing air over the main wing, and a control system. The control system comprises data storage having instruction code stored thereon that, when executed by one or more processors of the control system, causes the control system to: after receiving a takeoff indication, increase thrust generated by the electric motor propellers to cause the craft to transition from a hull-borne mode of operation to an airborne mode of operation, and after a thrust adjustment condition occurs, increase thrust generated by the combustion motor propellers.

The invention provides a multi-mode intelligent propulsion control method, device and equipment for a short vertical aircraft and a storage medium, and the method comprises the steps: firstly obtaining flight state data in real time, and classifying the flight state data according to a state classification model of a decision tree to generate a current flight mode; next, calling a control strategy group and performing parallel processing on the current flight mode by taking the lowest energy consumption as an optimization target so as to generate a plurality of control instructions, and calling a fusion device weight network to process the current flight mode so as to generate a fusion weight of each control instruction, and generating a final control quantity according to the plurality of control instructions and the fusion weight, and sending the final control quantity to a pre-constructed hybrid propulsion structure nonlinear model to control the short vertical aircraft, thereby solving the problem that the short vertical aircraft cannot be adaptively adjusted when a plurality of propulsion units have differential dynamic characteristics.

The invention relates to the field of aircraft intelligent control, and discloses a sensor fault resistant low-altitude aircraft multi-mode propulsion control method, which comprises the following steps: constructing a nonlinear model of a short-vertical aircraft hybrid propulsion system, taking deep exploration optimization reinforcement learning as a main control, and combining a fuzzy controller and a model prediction controller to form a strategy fusion group; the method comprises the following steps: introducing a residual perception mechanism and a GIRLS-EKF health estimation module, extracting residual signal features by using CNN and Transform, and carrying out real-time diagnosis and dynamic weight adjustment on an abnormal measurement state of a sensor in combination with generalized residual least square filtering and an extended Kalman structure; the controller fusion module outputs the optimal control quantity in a self-adaptive manner according to the health state and the flight mode, and the fault-tolerant performance and the energy efficiency scheduling capability of the multi-propulsion system under the complex working condition are improved; the method is suitable for low-altitude economy and urban air traffic task scenes, and has good engineering integration and intelligent control application prospects.

A hybrid propulsion system for an electric aircraft, the system including an electric aircraft including a fuselage. The fuselage including an energy source containing electric power. The electric aircraft further including at least a laterally extending element attached to the fuselage and extending laterally from the fuselage. The electric aircraft further including at least a propulsor electrically connected to the energy source. The system also including at least a power unit pod attached to the at least a laterally extending element and including an auxiliary power unit configured to generate electric power. The power unit pod also including a fuel tank in fluid communication with the auxiliary power unit and a power output line electrically connected to the energy source of the electric aircraft.

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 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.

Systems and methods for controlling flight via a parallel hybrid aircraft having an electric propulsion system and a combustion propulsion system are disclosed. Exemplary implementations may include: a combustion propulsion system including a combustion engine; an electric propulsion system including a motor and an electric power source, wherein the motor comprises a stator, a rotor coupled to the engine shaft, and support bearings between the rotor and the stator; a mechanical link coupled to the stator and the combustion engine, wherein the mechanical link substantially prevents movement of the stator in a rotational degree of freedom; and a propeller coupled to the engine shaft, wherein the rotor is coupled to the engine shaft between the propeller and the combustion engine.

The invention relates to the technical field of bionic robotic fishes, and discloses a bionic fish fin, a bionic robotic fish and a wave-beat multi-mode hybrid propelling method.The wave-beat integrated propelling flexible fin propelling device comprises a supporting frame and a plurality of unit pieces sequentially arranged on the supporting frame; the first ends of the unit pieces are connected to the power output end of the flexible fluctuating motion driving device, every two adjacent unit pieces are arranged in an included angle mode, the multiple unit pieces are arranged in a wave shape, the second ends of the unit pieces are controlled to swing up and down in the vertical direction through the flexible fluctuating motion driving device, and then the multiple unit pieces are controlled to conduct flexible fluctuating motion in a wave shape. The wave-beat integrated propelling flexible fin propelling device is arranged at the power output end of the flapping motion driving device, the whole wave-beat integrated propelling flexible fin propelling device is controlled by the flapping motion driving device to swing up and down in the vertical direction, and therefore flapping motion is achieved. The multi-modal propulsion integrating fluctuation and flapping can be realized, and three-dimensional high maneuverability and low disturbance are realized.

The present invention relates to saddle-ride type vehicle, motorcycle or motorbike, comprising a frame (2), at least a steering wheel (3) rotatably connected to the frame and a single driving wheel (4). The vehicle further comprises a motor assembly (10) and a transmission unit (T) that mechanically connects the motor assembly (10) to the driving wheel. The motor assembly comprises a thermal engine (MT) including a crankshaft (11), an electric machine (E) including a stator (S) and a rotor (R), and a clutch (C) including a driving shaft (C1) and a driven shaft (C2). The motor assembly (10) further comprises a gearbox (G) provided with an input shaft (111) and an output shaft (112). According to the present invention the crankshaft (11) of the thermal engine (MT), the rotor (R) of the electric machine (E) and the two shafts (C1, C2) of the clutch are coaxial so as to rotate around a common rotation axis (101) which is parallel to a longitudinal direction (Y) of the vehicle and parallel to the rotation axis of the output shaft (112) of said gearbox (G).

The present invention relates to a hybrid-electric propulsion system for aircraft, specifically a propulsion system utilizing a propulsor driven by both an internal combustion engine and an electric machine. The hybrid-electric propulsion system includes an internal combustion engine such as a gas turbine, an electric machine (either motor or generator), and various subsystems including a thermal management subsystem for cooling flows, an electrical power supply system, a control system, and an electrochemical storage system.

A hybrid propulsion update system includes a controller in signal communication with a replaceable battery. The controller includes a tuning parameters storage unit configured to store at least one tuning parameter corresponding to the replaceable battery. The controller is configured to execute at least one optimization algorithm that utilizes the tuning parameters to control operation of the hybrid electric aircraft according to a first performance. The tuning parameters storage unit is configured to receive at least one updated tuning parameter from a controller updating device. The controller executes the at least one optimization algorithm that utilizes the at least one updated tuning parameter such that the hybrid electric aircraft operates according to a second performance that improves upon the first performance.

The invention discloses an air-ground conversion power matching optimization method for a hybrid propulsion system, which comprises the following steps of: 1, constructing an air-ground conversion working condition identification method of a hovercar, and monitoring the speed, acceleration, attitude angle, tire pressure and propeller rotating speed parameters of the hovercar in real time through various sensors; step 2, calculating power requirements of land driving and air flight based on a working condition identification result in the step 1; 3, formulating an air-ground switching strategy according to a power demand calculation result in the step 2; and 4, based on the optimization strategy in the step 3, establishing a feedback control mechanism, monitoring a power matching effect in real time, and adjusting a power distribution strategy according to a specific optimization requirement of a working condition to ensure an optimal state of power matching under different conversion working conditions. By optimizing the power distribution strategy, efficient and stable air-ground conversion of the system under different working conditions is ensured, and the energy utilization efficiency and safety of the hovercar are improved.

The invention provides a compact medium-temperature fuel cell jet engine multi-mode split hybrid propulsion system, and aims to improve the efficiency of an aircraft propulsion system and reduce environmental pollution. Compared with a traditional engine, the engine adopts the parallel double-shaft design, flexible transmission and distribution of power are achieved through the bevel gears and the clutches, and two working modes are supported to drive a fan, namely, a shaft driving mode and an electric driving mode. And in the medium temperature mode, the engine abandons a high-pressure compressor, and air treated by a low-pressure compressor is directly sent to the cathode of the fuel cell, is heated together with mixed gas obtained after combustion of hydrogen and oxygen, and then enters the anode. The invention also considers the configuration of the galvanic pile, and adopts a hollow cylinder configuration, so as to increase the reaction area and improve the thermal management. And meanwhile, the slender structure optimizes the space utilization, so that the overall layout is more compact. The coupled lower structure allows integration of a plurality of motors, facilitating heat dissipation and maintenance. And the shell cover provides protection for the internal structure, so that the durability and the safety are enhanced. Through the innovative design, the engine has remarkable advantages in the aspects of improving the heat efficiency, reducing the oil consumption rate and reducing NOx emission, and has important significance on environmental protection and development of the aviation propulsion technology.

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 invention provides a multi-mode split hybrid propulsion system of a compact high-temperature fuel cell jet engine. The problems that a traditional aviation gas turbine engine is low in heat efficiency, high in oil consumption rate and high in nitrogen oxide emission amount are solved. The device comprises a propelling system, a transmission system and a lubricating system, the propelling system adopts parallel double shafts; the two connecting shafts can transmit power through a transmission system, so that two working modes of the ducted fan are realized; and the lubricating system feeds lubricating oil to all shaft systems on the shaft. The high-temperature solid oxide fuel cell system supplies power to the motor through the direct current conversion device, then the motor drives the ducted fan, and the total efficiency and the total thrust of the hybrid propulsion system are improved. The hydrogen-rich combustion chamber and the hydrogen-poor combustion chamber are additionally arranged on the structure, so that the problem that the high-temperature solid oxide fuel cell needs a heat exchanger with a complex pipeline to preheat fuel is solved.

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 derived from the gas turbine engine 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 forward propulsion of the aircraft and a respective electrical machine each configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.

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.

A hybrid propulsion system including a turbine engine including a high-pressure spool and a low-pressure spool, the low-pressure spool including reduction gear, the reduction gear forming part of a transmission gearbox which is positioned axially at a front end of the propulsion system; —first and second electric machines mechanically and respectively connected to the high-pressure and low-pressure spools, the electric machines being configured to operate in modes referred to as motor and generator, the first and second electric machines being fixed to the transmission gearbox; —a control system which is configured to allow the transfer of power between the high-pressure and low-pressure spools via the first and second electric machines.

A method and system for operating a hybrid propulsion system, includes controllably providing a first power to a first bus and a first inverter, electrically coupling a first motor with a second inverter by way of a second bus, operably converting, by the second inverter, the first power received by the first inverter to a starting power adapted for starting the first motor, and increasing, by the second inverter, the starting power to match the first power received.

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.

A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system. The ECU can be configured to receive a torque command and split output power between the electric motor system and the heat engine system. Additionally and / or alternatively, the ECU can be configured to balance a total torque against a second total torque of a second aircraft powerplant.

A method and system for operating a hybrid propulsion system, includes controllably providing a first power to a first bus and a first inverter, electrically coupling a first motor with a second inverter by way of a second bus, operably converting, by the second inverter, the first power received by the first inverter to a starting power adapted for starting the first motor, and increasing, by the second inverter, the starting power to match the first power received.

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 distributed hybrid propulsion system is provided and includes an engine assembly that includes an engine, which is non-propulsive, an energy storage element, a motor-generator and a common bus to which the engine assembly, the energy storage element, the motor-generator and the controller are connected. The common bus includes bi-directional power flow control elements, which are controllable to manage bi-directional power flow between the engine assembly, the energy storage element and the motor-generator.

A system for controlling a hybrid propulsion system includes a computer programmed to obtain altitude and terrain information associated with a predetermined route for the hybrid propulsion system comprising a first energy source and a second energy source. The computer is also programmed to obtain current and forecast ambient weather information associated with the predetermined route of the hybrid propulsion system, determine a power requirement and a torque requirement of the hybrid propulsion system associated with the altitude and the terrain along the predetermined route of the hybrid propulsion system, generate a trip plan to optimize at least one of a plurality of performance parameters of the hybrid propulsion system as the hybrid propulsion system travels along the predetermined route, and preferentially select the first energy source and / or the second energy source based on the trip plan.

Propulsion system for a helicopter comprising a main engine, a main rotor, a main gearbox including an output mechanically connected to the main rotor, a reduction gearbox mechanically coupled between the main engine and a first input of the main gearbox, and an assistance device. The assistance device comprises a first electric machine mechanically coupled to the reduction gearbox and configured to operate as an electric generator to take off energy produced by the main engine, and a second electric machine mechanically coupled to a second input of the main gearbox, the second electric machine being supplied with electrical power by the first electric machine and configured to operate as an electric motor to deliver additional mechanical power to the main gearbox.

The invention discloses a hybrid propulsion system air-ground load adaptive power following optimization method, which comprises the following steps: 1, in the operation process of a hovercar, firstly constructing an air-ground state signal acquisition method through various sensors, and carrying out data processing by taking power requirements under different environmental conditions as targets; 2, based on the power demand real-time monitoring and vehicle speed, height, acceleration and environmental condition change conditions in the step 1, establishing a power distribution model under the conversion between an air flight state and a ground driving state; 3, obtaining a power distribution relation based on the air-ground state signal and the state information of the piston engine and the motor based on the motor torque and the engine rotating speed in the step 2; and 4, further optimizing power distribution through a real-time feedback control strategy on the basis of the step 3. By adjusting power output in real time, self-adaptive response to load changes is achieved, and therefore the overall operation efficiency and safety of the hovercar are improved.

The solid oxide fuel cell with combustor (SOFC-C) addresses the problems of fast start-up, high gravimetric power density and emission control facing SOFC in aerospace and other mobile vehicle applications by providing a highly efficient clean power generation for full or partial hybrid propulsion systems. The SOFC-C may include one or more SOFC tubes and a combustion chamber integrated within a housing. Fuel may be provided through an anode portion of the one or more SOFC tubes or stacks and be combusted upon exiting the one or more SOFC tubes or stacks. The combustion products may then be provided through a cathode portion of the one or more SOFC tubes or stacks, whereby pollutants may be reduced or removed from the combustion products by the cathode portion prior exiting the housing as exhaust. A cathode inlet temperature may be controlled by controlling the fuel flow.

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.