129 results about "Starter generator" patented technology

The invention discloses an electric energy management system and method for a multi-electric aero-engine, which are mainly suitable for comprehensive electric energy management of the multi-electric aero-engine. The system is mainly composed of a starter generator unit, a high-voltage energy storage unit, a power supply and distribution control unit and an electricity load unit. The management method comprises the steps of power supply framework initialization, starting power supply control, operation power generation switching, fault emergency processing and the like. A power supply and distribution centralized management mode is adopted, high and low voltage direct current buses are configured, all power supplies supply power to the buses, all loads take power from the buses, and the power supply and taking process is controlled by a power distribution unit. Aiming at control management of a multi-electric aero-engine power supply, an electric load and the like, reasonable, reliable and safe electric energy distribution management is performed on electrified equipment such as a starter generator, an energy storage battery, the electric load and the like through the electric energy management system, the energy conversion efficiency is improved, the weight of accessories is reduced, and the system is simple and easy to control; the engine working performance is improved.

The embodiment of the invention discloses a multiplex type three-stage starting power generation controller, and relates to the technical field of aviation three-stage starting power generators. In the starting stage, an H-bridge inverter in the starting power generation controller provides single-phase alternating-current exciting current for a main exciter stator exciting winding through SPWM modulation so as to establish a pulsating magnetic field to provide exciting current for a main motor, and a three-phase full-bridge inverter provides armature current for a main motor stator armature winding through SVPWM modulation. In a power generation stage, an anti-parallel diode of the three-phase full-bridge inverter is used as a rectification circuit of the auxiliary exciter, and the H-bridge inverter adopts a PWM chopping mode to operate as an asymmetric half-bridge circuit. A power generation controller and a starting controller are integrated into a whole, and by changing the modulation mode of a hardware circuit, the control function of the three-stage starting generator at different stages can be realized by only one controller, so that the structure of the starting power generation controller is simplified, the system integration degree of the three-stage starting generator is improved, and the volume and the weight of the system are reduced.

The utility model provides an oil-electricity hybrid power control system, which is suitable for a vehicle and comprises a storage battery, an integrated starter generator coupled to the engine; the hybrid power controller is used for receiving at least one of an accelerator opening degree signal, a brake signal, an engine rotating speed signal, a storage battery voltage signal, a starting signal and an idling stop signal and determining whether to perform one of a starting mode, a charging mode, an auxiliary power judgment mode, a regenerative charging judgment mode and an idling stop judgment mode according to the at least one of the accelerator opening degree signal, the brake signal, the engine rotating speed signal, the storage battery voltage signal, the starting signal and the idling stop signal; when the hybrid power controller is in a charging mode, the integrated starter generator is driven by the engine to generate and output a first AC voltage to the hybrid power controller, so that the hybrid power controller performs switching voltage regulation control according to the first AC voltage to generate output power to charge the storage battery and the vehicle load.

The invention discloses an aviation starter generator with an internal cleaning function, and relates to the technical field of starter generators, the aviation starter generator comprises a machine body and a motor shaft, the motor shaft is rotatably mounted in the machine body, a rotor is arranged on the motor shaft, a stator is arranged in the machine body, two air ports are formed in the machine body, and two air filter assemblies are symmetrically arranged in the machine body. The two air filter assemblies are located on the outer sides of the stator and the rotor, the motor shaft is provided with the two sealing assemblies, the two sealing assemblies are located in the two air openings correspondingly, the two sealing assemblies are located on the outer sides of the two air filter assemblies, when the motor shaft operates, the sealing assemblies open the air openings, one air filter assembly extracts external air and guides the filtered air into the machine body, and the other air filter assembly is located on the outer side of the machine body. And the other air filtering assembly discharges air carrying heat out of the machine body from the air port. When the motor shaft rotates in a reversing mode, the wind filtering assembly discharges filtered dust and chippings generated by bearing operation out of the machine body, and cleaning and heat dissipation of the interior of the starting generator are achieved.

A power converter system includes an asynchronous induction generator electrically coupled to an inverter / converter / controller (ICC). The ICC is coupleable to an electrical load. The ICC can include an AC-DC converter and a DC-DC converter. The DC-DC converter is configured to operate at a duty cycle substantially equal to 1 in a first operating mode. In the event of a short-circuit fault in the electrical load, the DC-DC converter is configured to operate at a duty cycle less than 1 in a second operating mode.

The power supply device includes a low voltage battery, a high voltage battery, a starter generator, a DC-DC converter, a changeover switch, and a controller. When an abnormality or a failure has occurred in the DC-DC converter, the controller controls the changeover switch to connect the starter generator to the other battery without via the DC-DC converter and controls the output of the starter generator corresponding to the connected other battery.

To obtain maximum performance and belt longevity, it is important that the belt is properly tensioned. In some scenarios such as hybrid vehicles where the belt is going through large variations in drive torque due to varying Belt Starter Generator (BSG) parameters due to regeneration and the like, a dynamic pivot may optimize belt tension for a variety of engine modes. In some embodiments a dynamic pivot dual arm tensioner may include a center arm having a first tensioning pulley journaled to the center arm and engageable with a mounting surface, such as an engine block or accessory bracket, through a mounting axis; a side arm having a second tensioning pulley journaled to the side arm and coupled to the center arm; a dynamic pivot around which the tensioner dynamically rotates; and the dynamic pivot journaled to the center arm.

The invention belongs to the technical field of aircraft electrical systems, and discloses an aircraft power supply system conversion control system and method. An important airborne part of an aircraft is connected with a bus bar; a ground power supply is connected with the first bus bar through a ground power supply contactor, a storage battery pack is connected with the bus bar through a storage battery pack contactor, and a starter generator is connected with the bus bar through a generator contactor and further connected with the storage battery pack through a generator switch. Wherein the storage battery pack contactor and the ground power supply contactor are connected and controlled by the ground power supply switch, and the generator contactor is connected and controlled by the starter generator controller; and a relay group is also arranged, and is connected with and controls all the contactors. The principle is simple and clear, conversion of a ground power supply, a generator and an emergency power supply can be achieved, and it can be guaranteed that the power supply system provides power for ground maintenance, engine starting, normal flight and emergency return flight of an airplane.

The utility model discloses a powder coating tool for the inner wall of a stator shell of a starter generator, which belongs to the technical field of starter generator manufacturing, and comprises a lower cover assembly and a mounting plate which are vertically arranged at an interval, and a plurality of guide rods are arranged between the lower cover assembly and the mounting plate; an air cylinder is arranged on the mounting plate, and a piston rod of the air cylinder is vertically arranged and connected with a mandrel assembly and an upper cover assembly; the lower cover assembly, the mandrel assembly and the upper cover assembly are ventilated and liquid-filled, the lower cover assembly and the upper cover assembly respectively blow away powder on upper and lower spigots and upper and lower end faces of a generator stator shell, and the mandrel assembly blows away powder on the inner wall and the upper portion of a pole shoe, so that the technical requirements of the powder coating process of the starting generator stator shell are met. In the whole powder coating machining process, an external cooling liquid source circulates in the lower cover assembly, the mandrel assembly and the upper cover assembly, the temperature, transmitted to the tool, of the stator shell of the starter generator is taken away, and the powder adhesion problem caused by overheating of the tool is avoided.

The invention discloses an all-electric engine self-powered system architecture and a control strategy thereof, and belongs to the field of aircraft power supply systems. The structure of the all-electric engine self-powered system is composed of an aero-engine, two starting generators, two sets of AC / DC starting power generation controllers, two 270V high-voltage DC bus bars, an electric energy storage device, a 28V low-voltage DC bus bar, a multi-port bidirectional DC / DC converter, a multi-port bidirectional DC / AC inverter, an oil pump motor and an electric actuator. The self-powered system is isolated from an external power supply system. And controlling the self-powered system according to the control strategy. The self-powered system architecture and the control strategy can effectively enhance the reliability and the stability of an engine key load power supply network, and improve the power supply quality of the power supply system; voltage fluctuation on the high-voltage bus bar is suppressed; energy feedback and efficient utilization are realized; the system cost and complexity are reduced, and the fault-tolerant capability and reliability of the self-powered system can be effectively improved.

The invention belongs to the technical field of starting control of an aviation starting and power generation integrated system, and particularly relates to a sensorless starting control method for an aviation three-stage type starting generator. The method comprises the following steps: estimating the initial rotating speed of starting with rotation by utilizing the voltage of a permanent magnet machine of a three-stage starter generator, starting according to the frequency of a given current vector and a corresponding current amplitude value of the rotating speed estimated by the voltage of the permanent magnet machine through I / f control, and estimating the rotor position of the three-stage starter generator through the counter electromotive force of a main generator at the same time; and when the rotor position estimated by the counter electromotive force coincides with the rotor position given by the I / f starting, the I / f starting is switched to the counter electromotive force position estimation through weighted switching, so that the non-position rotation starting function of the three-stage starter generator is realized.

The present disclosure relates to a system (100) and a method (400) for providing reverse riding assistance to a rider of a vehicle (140). The system comprises one or more sensors (102) adapted to procure information pertaining to one or more operating parameters of the vehicle. An integrated starter generator (ISG) (122) is coupled to an engine (124) of the vehicle. A control unit (128) is communicatively coupled to each of the one or more sensors and the ISG. The control unit is configured to: receive an input from the rider for reverse riding assistance; compare the one or more operating parameters with one or more predetermined operating conditions of the vehicle; and operate the ISG to provide reverse assistive torque to the engine for the reverse riding of the vehicle, when the one or more operating parameters corresponds to the one or more predetermined operating conditions.

The invention relates to a power converter and a system for an engine starter generator. A power converter system includes an asynchronous induction generator electrically coupled to an inverter / converter / controller (ICC). The ICC may be coupled to an electrical load. The ICC may include an AC-DC converter and a DC-DC converter. The DC-DC converter is configured to operate at a duty cycle substantially equal to 1 in a first mode of operation. In the event of a short-circuit fault in the electrical load, the DC-DC converter is configured to operate at a duty cycle of less than 1 in the second mode of operation.

This invention belongs to the field of new energy vehicle technology, and particularly relates to a multi-functional power domain control system and control method for new energy vehicles. The system includes a main control module configured to control the engine management module and / or the automatic transmission electronic control module and / or the shift control module and / or the hybrid vehicle control module and / or the air conditioning module and / or the thermal management module for battery and motor temperature and / or the accelerator pedal module and / or the traction motor control module and / or the integrated starter generator control module and / or the DC-DC converter module and / or the slow charging module and / or the fast charging module to perform corresponding functions. This enables direct electrical connection between each functional module in the new energy vehicle and the main control module. Each functional module can directly send detected parameter data to the main control module, avoiding delays caused by sequential data transmission. The main control module can immediately feed back corresponding control signals based on the acquired parameter data.

An aircraft starting generator detection system comprises a generator dragging platform connected with an aircraft generator to be detected, the generator dragging platform is electrically connected with a speed regulation power distribution cabinet, a frequency converter is arranged in the speed regulation power distribution cabinet to drive the generator dragging platform, the speed regulation power distribution cabinet is controlled by a test bench, and the output end of the aircraft generator to be detected is electrically connected with a load box. The test bench carries out data sampling on the frequency converter, the generator dragging platform, the to-be-detected aircraft generator and the load box. Meanwhile, the system is further provided with an adjustable load device and a wide-range rotating speed controller so as to meet the requirements under different test conditions, and the system has the advantages of being comprehensive in detection parameter, convenient in load adjustment, large in rotating speed range, safe, reliable and the like. Defects in an existing aircraft generator detection system can be effectively overcome, the comprehensiveness and accuracy of a detection result are improved, and a powerful guarantee is provided for safe flight of an aircraft.

The invention belongs to the technical field of aviation power generation systems, and discloses an alternating current starting power generation system starting phase sequence online identification method, which comprises the following steps of: 1, providing 28V control electricity and 115V / 400Hz three-phase constant-frequency alternating current for a generator controller; 2, setting a current comparison threshold value, wherein a data acquisition period is as follows; the starting generator controller is used for converting the 115V / 400Hz three-phase constant-frequency alternating current into low-voltage three-phase constant-frequency alternating current; 3, applying the low-voltage three-phase constant-frequency alternating current to a three-phase winding of a main generator stator to generate three-phase current; step 4, collecting three-phase current fed back by a current sensor, and recording the three-phase current as,..., and collecting three-phase current fed back by a motor mutual inductor, and recording the three-phase current as,...; 5, calculating the sum of the three-phase current according to the sum; and 6, calculating the absolute value of the current sum in one current period, solving the average value of the absolute values of continuous N periods, if the average value is smaller than a set threshold value, indicating that the starting phase sequence is correct, otherwise, indicating that the starting phase sequence is wrong.

This patent discloses a power supply method and system for hybrid aircraft, belonging to the field of aviation electrical systems. It is used to solve the problem of integrating the high-voltage and low-voltage power grids of hybrid aircraft. On the one hand, it realizes efficient electric propulsion and significantly reduces fuel consumption. On the other hand, it uses an energy storage device to combine the electric propulsion system with starting and generating technology, improving the system's integration and reuse capabilities. The power supply system of the present invention includes: an energy storage device, a hybrid generator, a starter generator, a prime mover, an electric propulsion system, and an electric energy distribution system.

The present invention discloses an aviation starter generator with an internal cleaning function, relating to the technical field of starter generators. The starter generator comprises a body and a motor shaft, wherein the motor shaft is rotatably mounted within the body, a rotor is disposed on the motor shaft, a stator is disposed within the body, two air vents are disposed on the body, two air filter assemblies are symmetrically disposed within the body, the two air filter assemblies are located outside the stator and rotor, and two sealing assemblies are disposed on the motor shaft, the two sealing assemblies are located in the two air vents, and the two sealing assemblies are located outside the two air filter assemblies. When the motor shaft is operating, the sealing assemblies open the air vents, one air filter assembly draws in external air and introduces the filtered air into the body, and the other air filter assembly discharges heat-carrying air from the air vents. When the motor shaft is reversing, the air filter assembly discharges filtered dust and debris generated by bearing operation out of the body, thereby achieving internal cleaning and heat dissipation of the starter generator.

The embodiment of the invention provides an engine torque rise control method and device, a vehicle and a storage medium, and relates to the technical field of engine control. The method comprises the steps that under the working conditions of speed changing, gear shifting and accelerator pedal loosening, a torque increasing request sent by a transmission control module is received, the torque increasing request comprises a target value, the available torque upper limit of a belt drive starting generator is determined, and the compensation value of torque increasing is determined based on the target value and the available torque upper limit; and controlling the torque of the belt-driven starting generator to increase the compensation value. According to the technical scheme provided by the embodiment of the invention, the available torque of the belt drive starting generator is utilized to realize torque rise, the engine does not need to execute oil injection and ignition operations, the response speed of torque rise is increased, and the oil consumption can be reduced.

The present invention relates to an engine assembly (100) for a motor vehicle. The assembly has a crankshaft (110) housed in a crankcase (120), a cam chain window (130) through which an oil path passes from a cylinder head to an oil sump in the crankcase (120), and an integrated starter generator (ISG) (200) having a rotor (210) rotatably mounted on one end of the crankshaft (110), the rotor having a plurality of protrusions (212) on a circumferential surface; wherein the circumferential surface of the rotor (210) receives oil from the cylinder head through the cam chain window (130) and the plurality of protrusions (212) splash the oil towards an inner wall (122A) of a crankcase cover (122) proximate to the ISG (200), thereby cooling the oil.

The embodiments described herein provide a system and method for using an integrated starter generator (ISG) for electric torque assistance in specific strokes of a 2-stroke or 4-stroke internal combustion (IC) engine (300) with reduced inertial mass compared to a conventional IC engine with inertial mass loading. This is intended to overcome a speed variation problem caused by the engine's lower inertia at low speeds and idle, thus compensating for the crankshaft's lower speed. Furthermore, allowing the 2-stroke and 4-stroke engines to operate with a lean fuel-air mixture improves emissions at low speeds and idle, leading to better control of IC engine emissions.

A method for starting a motorcycle engine is performed through an engine starting control system including a controller, a power supply apparatus coupled to the controller, and an integrated starter and generator coupled to the controller, the power supply apparatus, and the motorcycle engine. The method includes driving the integrated starter and generator to perform reverse operation at a reverse operation constant torque value within a reverse operation time until the reverse operation time ends; controlling the power supply apparatus to output a forward operation constant current to the integrated starter and generator after the integrated starter and generator stops the reverse operation, to perform forward operation; and starting the motorcycle engine through the integrated starter and generator when a forward operation angular velocity value is greater than or equal to an expected value. The method starts the motorcycle engine effectively. Furthermore, a corresponding system is also provided.

A power supply system (100) for an aircraft, comprising: a plurality of main generators located in a left channel and a right channel; an auxiliary power unit (APU) starter generator (ASG) located in the right channel and configured to supply power when the main generators fail; a plurality of transformer rectifier units (TRUs) located in the left channel, the right channel and an emergency channel; a plurality of autotransformer units (ATUs) located in the left channel, the right channel and the emergency channel; and a ram air turbine (RAT) located in the emergency channel. The present invention further relates to a method for using a power supply system to supply power an aircraft.

The invention relates to the technical field of motor rotor side current estimation, in particular to a multi-stage starter generator rotor side current estimation method considering iron loss influence, which comprises the following steps: constructing an equivalent iron loss resistance database; obtaining a current excitation current effective value and equivalent iron loss resistance corresponding to the current excitation current effective value in an equivalent iron loss resistance database; obtaining the rotor three-phase current of the main exciter under the static three-phase coordinate system; and obtaining the rotor current of the main motor. According to the method, the problem that the rotor side current cannot be measured due to a brushless excitation structure of the multi-stage starter generator is solved, the current estimation effect is not influenced by the iron loss change of the main exciter, and the problem that when the main exciter has large iron loss, the estimation current is large due to the fact that the iron loss is ignored in a traditional method is solved; therefore, the accuracy of current estimation is improved.

Motor vehicle drive device for connecting an internal combustion engine (1) to an electromechanical energy converter (2), wherein this energy converter is configured for starting the internal combustion engine, and with a starter-generator transmission (5) comprising a first drive train (3) which is configured for transmitting a torque from the electromechanical energy converter (2) to the internal combustion engine (1) when starting the internal combustion engine and wherein this transmission (5) has a reduction gear ratio in the direction from the electromechanical energy converter (2) to the internal combustion engine (1) and comprising a second drive train (4) which is configured for transmitting a torque at least temporarily in the direction from the internal combustion engine (1) to the electromechanical energy converter (2) and wherein the second drive train (4) is arranged parallel to the first drive train (3) with respect to the torque transmission between the electromechanical energy converter (2) and the internal combustion engine (1), characterized by the fact that the first drive train (3) has a one-way coupling which is arranged such that a torque can be transmitted from the electromechanical energy converter (2) to the internal combustion engine (1) via this drive train (3) when the internal combustion engine (1) is started and that the second drive train (4) has a speed-sensitive clutch (6) which is open until a first speed threshold is reached, so that in this state no torque can be transferred from the internal combustion engine (1) to the electromechanical energy converter (2) via the second drive train (4) and that the speed-sensitive clutch (6) is closed from the moment this first speed threshold is exceeded and that the one-way clutch makes it possible, during the phases in which the internal combustion engine alone or together with the starter generator provides drive power for the propulsion of the motor vehicle, that the starter generator gearbox is only running freely, meaning no power can be transmitted through it.

The invention relates to a method for operating a hybrid electric vehicle (2), at least comprising the following steps: (S1400) Reading a battery state value (BSV) indicative of the state of a traction battery (28) of the hybrid electric vehicle (2) and comparing the battery state value (BSV) with a battery state reference value (BSR), and (S1500) Activating an eEGH (20) of the hybrid electric vehicle (2) when the battery state of charge (BZW) is greater than the battery state of charge reference (BZR), and / or (S28 00) Reading a temperature value (TW) indicative of an ambient temperature of the hybrid electric vehicle (2) and comparing the temperature value (TW) with a temperature reference value (TR), and (S1700) Starting an internal combustion engine (6) of the hybrid electric vehicle (2) with a starter generator (14) of the hybrid electric vehicle (2) when the temperature value (TW) is greater than the temperature reference value (TR), and / or (S2900) Starting an internal combustion engine (6) of the hybrid electric vehicle (2) with a starter (16) of the hybrid electric vehicle (2) when the temperature value (TW) is less than the temperature reference value (TR).

The application discloses a three-stage starting generator rotor position estimation method suitable for a single-phase exciter, and belongs to the field of motor control. The method estimates the rotor d-axis current and extracts its outer envelope by applying an alternating voltage on the exciter stator side and collecting the stator current. The outer envelope crest and trough are detected to generate the discrete position state of the exciter. The discrete state of the main motor is generated according to the pole pair ratio and the duration is recorded. The discrete rotor position of the main motor and the interval average speed are calculated accordingly. The continuous rotor angle is obtained by using the previous interval speed compensation, and the real-time rotor position is obtained by combining the initial position. The application can realize high-precision estimation of the rotor position of the main motor by using only the electrical signal characteristics of the single-phase exciter itself, without the need for a mechanical position sensor. The application solves the problem that the existing method cannot be applied to the single-phase exciter structure, and has good stability and robustness in severe environments such as aviation high temperature and high pressure, strong electromagnetic interference and the like.

A method to reset an electromechanical disconnect is provided. The method includes electrically disengaging a pawl holding a first half of a dog clutch, located between a starter-generator and a main engine gear box, in a disengaged position, controllably energizing the starter-generator to produce a selected angle of rotational motion of a starter-generator shaft, wherein the selected angle is equal to 360 degrees divided by a number of teeth on the first half of the dog clutch, and determining when the first half of the dog clutch is engaged with a second half of the dog clutch.

The utility model discloses a motorcycle idling start-stop controller with dormancy control, which comprises a dormancy control module, a Hall power supply module, a half-bridge driving module, a CAN (controller area network) communication module, a start power generation motor, an MCU (microprogrammed control unit) and a power switch for controlling a vehicle power supply, the Hall power supply module, the half-bridge driving module and the CAN communication module are electrically connected with the dormancy control module, the starting power generation motor is provided with a Hall sensor, the MCU is electrically connected with the dormancy control module and the Hall sensor, and the Hall power supply module can supply power to the Hall sensor when the power switch is closed. The MCU can detect the working state of the starting power generation motor through the Hall sensor, and the dormancy control module can control the Hall power supply module, the half-bridge driving module and the CAN communication module to enter a dormancy mode according to a received dormancy electric signal. The energy-saving device is good in energy-saving effect.

The invention provides a starting method and device of a micro gas turbine, a storage medium and an electronic device.The method comprises the steps that a starting signal of the micro gas turbine is responded, a starting generator is started and enters a first starting stage, and in the first starting stage, the rotating speed of the starting generator is controlled to rise through open loop, the starting generator is connected with the micro gas turbine through a coupling; in the first starting stage, collecting a first bus voltage and a first phase current of the generator in real time; based on the first bus voltage and the first phase current, controlling the starting generator to switch from the first starting stage to a second starting stage; and in the second starting stage, the rotating speed of the generator is continuously increased through closed-loop control to reach the ignition rotating speed of the micro gas turbine. According to the embodiment, the technical problem that in the prior art, starting of the micro gas turbine is controlled through a position sensor, and the occupied space is large is solved, and the cost and the size of a power generation system are reduced.