233 results about "Starter generator" patented technology

The invention relates to an electrical fault diagnosis method for a full-stage excitation system of a multi-stage starter generator, which comprises the following steps of: firstly, acquiring stator current of an exciter and calculating vector amplitude of the stator current, and then solving characteristic quantities such as an average value, a half-cycle average value, a ratio of a minimum derivative value to a maximum derivative value and the like of the vector amplitude of the stator current; the method is used for electrical fault diagnosis of the full-stage excitation system of the multi-stage starter generator. The method provided by the invention can diagnose whether the excitation system (comprising an exciter stator winding, an exciter rotor winding, a rotating rectifier and a main motor excitation winding) of the multi-stage starter generator has an electrical fault or not and the fault type on line at the static stage, the starting stage and the power generation stage of the system. The method has important significance for improving the operation reliability and the maintenance convenience of the multi-stage starting power generation system. The method provided by the invention can diagnose whether each component of the excitation system of the multistage starter generator has an electrical fault or not on line at the static stage, the starting stage and the power generation stage of the system, and judges the fault type.

The present invention relates to a method for diagnosing secondary faults of a rotating rectifier of a multi-stage starting generator. If a single diode open circuit fault occurs in the rotating rectifier when the multi-stage starting generator is in the power generation stage, the system can be derated and run "with the fault". However, a single diode open circuit will cause the three bridge arms of the rotating rectifier to no longer be balanced, thereby increasing the risk of secondary faults. The method proposed in the present invention performs secondary fault diagnosis of the rotating rectifier based on the maximum point distribution characteristics of the voltage waveform at the idle winding end of the stator of the exciter. The proposed method makes full use of the idle excitation winding of the exciter when the system is in the power generation stage. The algorithm is simple and can diagnose the secondary faults of the rotating rectifier online in real time.

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 invention relates to a multi-stage starter generator rotating part electrical fault online diagnosis method, and provides a multi-stage brushless synchronous starter generator rotating part electrical fault online diagnosis and positioning method based on exciter rotor current characteristics. The method comprises the following steps: firstly estimating three-phase current of an exciter rotor, and then carrying out a series of processing such as absolute value taking, average value taking, normalization and fundamental wave filtering on the estimated rotor current to obtain characteristic quantities such as a maximum ratio difference and a minimum approximate difference for electrical fault diagnosis and positioning of the rotating part of the multi-stage starter generator. The method provided by the invention can diagnose whether the rotating parts (including an exciter rotor winding, a rotating rectifier and a main motor excitation winding) of the multi-stage starter generator have electrical faults on line, and can judge the fault type (open-circuit fault or short-circuit fault) and the specific position of a fault point. The method is beneficial for improving the operation reliability and the maintenance convenience of the multi-stage starting power generation system.

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.

A variable frequency starter generator (VFSG) system includes a VFSG having a start mode and a generate mode, a permanent magnet generator (PMG) and a main generator section and an exciter section. The system also includes a controller electrically connected to the VFSG. The controller flow start mode three phase electrical power from aircraft power to the exciter of the VFSG in the start mode and flows single phase electrical power to the exciter of the VFSG in the generate mode. The controller includes: an input active rectifier that receives input AC power and converts it to DC power and provides it to across a positive rail and negative rail; an output inverter coupled to an output of the input active rectifier; and one or more line inductors connected along one or both of the positive rail and negative rail between the input active rectifier and the output inverter.

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 utility model relates to an aviation starter generator and a connecting structure of a hollow shaft and a flexible shaft thereof, belongs to the technical field of aviation starter generators, and solves the problems of high processing time and cost and poor interchangeability in the prior art. According to the utility model, the flexible shaft comprises a first end and a second end, and the first end extends into a central through hole of the hollow shaft from the front end of the hollow shaft; a plurality of annular bosses are arranged on the peripheral surface of the flexible shaft; a central through hole of the hollow shaft is a stepped hole, and the annular bosses are respectively in clearance fit with one section of the stepped hole so as to ensure the coaxiality; a flat key is arranged between the flexible shaft and the hollow shaft to transmit torque; the hollow shaft and the flexible shaft are axially limited by adopting two step surfaces and are fastened by adopting bolts. The two annular bosses are adopted for guaranteeing coaxiality, the two step faces and the bolts are adopted for axial limiting, and the flat keys are adopted for transmitting torque, so that connection reliability is guaranteed, manufacturing difficulty and machining cost are reduced, and meanwhile rapid maintenance and replacement of the flexible shaft are achieved.

The invention provides a starting control method of an aircraft auxiliary power device. The aircraft auxiliary power device comprises an APU working state electronic regulator, an APU automatic starter, an APU starting box and an engine starting accessory. The APU starting box is connected with the starting generator; the method comprises the steps that when an APU automatic starter receives an aircraft APU starting instruction, the working time sequence of an engine starting accessory is controlled according to a set program, the APU automatic starter is matched with an APU starting box, and the output power of a starting generator is controlled in a grading mode through armature series resistor voltage reduction starting, full-voltage starting and weak magnetic speed regulation, so that the requirement for starting the engine is met, and the starting efficiency is improved. The purpose of smoothly starting the engine is achieved in a low-power-consumption and quick-starting mode.

The invention discloses a rotor position estimation method under initial turn-to-turn short circuit of an aviation permanent magnet starter generator, and the method specifically comprises the steps: obtaining a correlation formula when a permanent magnet synchronous motor is in a healthy state and a turn-to-turn short circuit fault occurs; on the basis of the turn-to-turn short circuit fault, voltage and current are obtained; inputting the three-phase current and voltage into a sliding-mode observer after the three-phase current and voltage are subjected to Click conversion to obtain back electromotive force; the back electromotive force is filtered, the positive sequence component is extracted, the fundamental wave back electromotive force is obtained, and accurate rotor position information can be estimated through a phase-locked loop. According to the method, when the aviation permanent magnet starter generator is operated in a power generation state without a position sensor, harmonic interference generated by a motor turn-to-turn short circuit fault is separated by designing a high-order generalized integrator, so that a positive sequence component in a fundamental wave back electromotive force estimated value is accurately obtained and is used for rotor position estimation after the turn short circuit fault occurs; the magnetic field orientation deviation caused by the turn short fault is eliminated, and the optimal fault feature extraction environment is ensured.

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.

A method of detecting belt slip in a starter system (10) for starting an internal combustion engine of a motor vehicle, the starter system (10) having a belt-driven integrated starter generator (11). In the event that the determined belt slip value exceeds a limit value, a control unit (20) of the motor vehicle evaluates the detection of belt slip, the belt slip value being determined to belong to a defined time window T which is opened after the internal combustion engine is started, and the belt slip value is determined to belong to the defined time window T after the internal combustion engine is started. The determination takes into account at least one acceleration value of the starter generator (11) within the time window T. The invention also relates to a motor vehicle having a control unit designed to carry out the method.

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.

The invention relates to electrical engineering, and more particularly to starter-generator devices for internal combustion engines. The technical result is achieved by optimizing and simplifying the design of a starter-generator. The present starter-generator comprises: a universal brushless DC machine and an electronic unit. The starter-generator consists of a rotor (1) and a stator (2) and is mounted directly on the engine shaft. The starter-generator is a brushless machine that is controlled by the magnitude of the back EMF, without the use of rotor position sensors. The electronic control unit (4) consists of two functional parts. One part is a control board for controlling the speed of rotation of the rotor of the brushless machine and is intended to allow the machine to operate in an engine start-up mode. The other part is a board for converting AC voltage to DC voltage and is intended to allow the brushless machine to operate as a generator. The brushless machine is switched from starter mode to generator mode by an electronic switching unit that is part of the control unit. The technical result is high starter-generator efficiency, a compact design and excellent reliability.

The invention discloses a magnetic conductance modulation type excitation generator containing position information of a main motor rotor, a rotor of the excitation generator is designed to be of an unequal-pole salient-pole magnetic conductance modulation structure, when the motor runs at a low-speed section, the unequal-pole magnetic conductance modulation type rotor structure is in a rotating state, magnetic conductance change of a magnetic circuit can be caused, and the magnetic conductance of the magnetic circuit can be changed. And therefore, the amplitude of the excitation current in the parallel branch at the stator side of the excitation generator is periodically changed, and the amplitude change is consistent with the number of salient pole structures of the rotor in a mechanical period. Through an amplitude demodulation method, an envelope line formed by amplitude change of excitation current can be utilized to demodulate rotor position angle information of the excitation generator contained in the envelope line. Furthermore, according to a three-stage starter / generator mechanical structure in which a main motor and a main exciter are coaxially installed, corresponding rotor position information of the main motor can be directly detected, and then the information is fed back to a control link, so that the motor is smoothly started, the signal extraction time is shortened, and the rotor position detection precision is ensured.

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.

Method for starting an internal combustion engine (2) of an internal combustion engine (1) with • at least one combustion chamber (3) of the internal combustion engine (2), • a fuel supply device for introducing fuel into the at least one combustion chamber (3), • an output shaft (11) of the internal combustion engine (2), • a pinion starter (19) which can be coupled to the output shaft (11), and • a starter-generator (23) which is connected to the output shaft (11) for drive purposes, wherein • the output shaft (11) during a first start-up phase from a standstill by means of at least the pinion starter (19) until a transfer speed (n) is reached U ) is accelerated, • the output shaft during a second start-up phase, which follows the first start-up phase, exclusively by means of the starter-generator (23) until a start-up speed (n) is reached S), which is greater than the transfer speed (n U ) is and is at least 500 rpm, is accelerated and • only once the starting speed has been reached (n S ) Fuel is introduced into the at least one combustion chamber (3) to initiate self-running of the internal combustion engine.

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.

The present invention relates to a power train of a plug-in hybrid vehicle using a multi-functional starter generator, and a control method using same, the power train of a plug-in hybrid vehicle comprising: an internal combustion engine unit (1); a motor-generator unit (2); a clutch unit (3); a transmission unit (4); a differential unit (5); a starter-generator unit (6); and a battery unit (8) connected to each of the motor-generator unit (2) and the starter-generator unit (6) through an inverter unit (7), wherein a first gear (12) is provided on an output shaft (11) of the internal combustion engine unit (1), a second gear (14) is provided on an input shaft (13) of the motor-generator unit (2), first and second dog clutches (21, 23) and third and fourth gears (22, 24) individually engaged with the first and second gears (12, 14) are provided on a driving shaft (25) of the starter-generator unit (6), the first dog clutch (21) connects or disconnects the driving shaft (25) of the starter-generator unit (6) to or from the output shaft (11) of the internal combustion engine unit (1) when the driving shaft (25) of the starter-generator unit (6) is synchronized with the output shaft (11) of the internal combustion engine unit (1), and the second dog clutch (23) connects or disconnects the driving shaft (25) of the starter-generator unit (6) to or from the input shaft (13) of the motor-generator unit (2) when the driving shaft (25) of the starter-generator unit (6) is synchronized with the input shaft (13) of the motor-generator unit (2).

The present invention provides a starter generator and a method for manufacturing the starter generator, which suppresses the increase in the number of processes and reliably discharges the sludge entering the clutch part to the outside by a simple method. The starter generator includes: a rotor having a yoke and a permanent magnet, the yoke having a cylindrical first side wall and a first bottom integrally provided with the first side wall, the permanent magnet being provided at the inner circumference of the first side wall; a flywheel having a second bottom and a cylindrical second side wall, the second bottom being provided on the side opposite to the first side wall relative to the first bottom, the second side wall extending from the second bottom to the side opposite to the first bottom; and a clutch part fixed to at least one of the second side wall and the second bottom, and the flywheel having: a recess provided at the second bottom and having an opening opening to the radially outer side of the second side wall; and a through hole formed from the inner surface of the second bottom and the second side wall toward the recess.

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.