2380 results about "Rotor (electric)" patented technology

The invention belongs to the technical field of aircraft design, and particularly relates to an integrated tilting power system integrated with hydrogen fuel cell motor electric control and an aircraft. Comprising a tilting mechanism connected with a machine body; the integrated motor and controller is fixedly connected with the tilting mechanism and located at the end, close to the upstream of the incoming flow, of the tilting mechanism; the tilting rotor wing is mounted at one end, close to the incoming flow upstream, of the integrated motor and controller; the hydrogen fuel cell is fixedly connected with the tilting mechanism and is positioned at one end, close to the downstream of the incoming flow, of the tilting mechanism; the nacelle shell wraps the tilting mechanism, the integrated motor, the controller and the hydrogen fuel cell; the nacelle outer heat dissipation fins wrap the nacelle in the circumferential direction; and the tilting mechanism, the integrated motor and controller and the liquid cooling radiating pipeline of the hydrogen fuel cell exchange heat with the radiating fins outside the nacelle.

A self-excitation motor disclosed by the present invention comprises a rotor, a first end of the rotor is equipped with a rectification circuit, the rotor comprises a rotor iron core and a plurality of harmonic windings and excitation windings, the rotor iron core is provided with rotor teeth, and each harmonic winding and each excitation winding are respectively wound on the corresponding rotor teeth. Each harmonic winding comprises a first harmonic winding and a second harmonic winding, the winding directions of the first harmonic winding and the second harmonic winding are the same, star connection is adopted, one ends of the first harmonic winding and the second harmonic winding are connected in series in a one-to-one mode, and the other ends of the first harmonic winding and the second harmonic winding are jointly connected to form a star neutral point; the other end of each second harmonic winding is connected with the midpoint of each bridge arm in the rectifying circuit in a one-to-one manner; the winding directions of the excitation windings on every two adjacent rotor teeth are opposite, and the two ends of each excitation winding are electrically connected with the direct current output end of the rectification circuit. This induces and rectifies the current for excitation more efficiently. The invention further provides a motor control strategy based on high-frequency harmonic current phase optimization.

The invention relates to the technical field of motor control, discloses a direct current brushless motor control method and system based on current prediction, and aims to solve the problems of large torque ripple, low efficiency and poor stability caused by current loop lag in the prior art. The method comprises the following steps: acquiring a motor operation state signal in real time; determining a sector and an electrical angular velocity based on the rotor position and the rotational speed; inputting related parameters into the mixed current prediction model to obtain a three-phase current prediction value of the next period; a prediction error is calculated in combination with a current instruction, and an optimal voltage vector enabling a cost function to be minimum is solved through a model prediction control algorithm; and finally, a space vector pulse width modulation signal is generated to drive an inverter. According to the method, advanced control is realized by fusing a physical model and a data-driven prediction mechanism, the torque ripple is remarkably reduced, and the energy efficiency and robustness are improved.

The invention relates to the technical field of fireproof equipment, in particular to an electrically-driven translation type heavy fireproof door which comprises a door body, a driving mechanism and a translation mechanism. The translation mechanism comprises a translation base and a nut sleeve, a mounting hole and a guide hole which penetrate through the two sides of the translation base are formed in the translation base, the nut sleeve and the lead screw form a thread transmission pair, the nut sleeve is rotatably mounted in the mounting hole, the guide rod is slidably connected in the guide hole, and a synchronous assembly is arranged in the translation base; when the door body moves to the tail end of the stroke, the circumferential constraint of the synchronous assembly on the nut sleeve is automatically relieved, so that the nut sleeve can freely rotate relative to the translation base. Therefore, the motor and the transmission system do not need to overcome the huge inertia of the door body to achieve forced stopping, the instantaneous load and locked-rotor risk of the motor are remarkably reduced, and meanwhile the impact stress borne by a mechanical transmission part at the terminal is greatly relieved.

The invention discloses an energy-saving air conditioner fan circulating water pump and a control method, and relates to the technical field of energy-saving household appliances, and the energy-saving air conditioner fan circulating water pump comprises a motor, a peristaltic pump shell, a peristaltic pump rotor and a centrifugal pump shell. The front end of the motor output shaft is connected with a fan; a plurality of extrusion wheels are arranged on the peripheral side of the peristaltic pump rotor, when the peristaltic pump rotor is in a first state, the extrusion wheels are matched with the peristaltic pump shell to extrude the elastic hose, the peristaltic pump rotor is in transmission connection with the output shaft, and when the peristaltic pump rotor is in a second state, the peristaltic pump rotor is separated from the output shaft; the extrusion wheel is separated from the elastic hose, the centrifugal pump shell is connected to the rear end of the peristaltic pump shell, an impeller is arranged in the centrifugal pump shell and connected to the rear end of the output shaft, the centrifugal pump shell is connected with a first water inlet pipe and a first water outlet pipe, and the first water outlet pipe is communicated with the water inlet end of the elastic hose. According to the centrifugal pump, one motor can be used for driving the fan and the impeller in the centrifugal pump shell, and energy consumption is reduced.

The invention relates to the technical field of motor detection, in particular to a generator set fault diagnosis and detection method based on deep learning, and the method comprises the steps: firstly, synchronously collecting three-phase voltage, current and rotating speed signals, and constructing a multi-dimensional time sequence matrix through data cleaning and sliding window segmentation; then, carrying out multi-scale decomposition on the matrix by adopting adaptive wavelet packet transformation, combining each frequency band reconstruction coefficient with an original signal channel, and constructing an enhanced feature tensor; then, a CNN-BiLSTM parallel network is constructed; and finally, dynamically fusing the features of the two branches through a self-adaptive weighted fusion strategy, and inputting a multi-layer full-connection classifier to output a fault type. According to the method, early weak fault features are effectively enhanced, bearing faults, rotor eccentricity, electrical imbalance and composite faults thereof can be accurately recognized, the intelligent level and accuracy of fault diagnosis of the generator set are remarkably improved, and the method can be widely applied to online monitoring and health management of power generation equipment of a power system.

A centrifugal separator arrangement includes: an energy converter positioned in proximity to a rotor of the centrifugal separator and configured to collect and convert the non-electrical energy generated by the rotor of the centrifugal separator into electrical energy; and a sensor configured to obtain a parameter associated with the operation of the centrifugal separator, wherein the sensor includes a processor configured to produce corresponding data, and wherein the sensor is in electrical connection with the energy converter to be powered by the electrical energy collected and converted by the energy converter. A method and a system for energy harvesting in the centrifugal separator arrangement is also provided.

A slip ring arrangement according to the invention for an electric machine comprises a first slip ring having a radial inner surface and a radial outer surface, a first contact pin forming an electrically conductive sliding contact with the first slip ring, a first conductor extending axially from the first slip ring and electrically connected to the first slip ring, and a substantially hollow cylindrical first support element having a radial inner surface and a radial outer surface. The first slip ring is arranged with its radial outer surface against the radial inner surface of the first support element. The first conductor is enclosed between the radial inner surface and the radial outer surface of the first support element.The first contact pin is guided radially displaceably within a second support element and is subjected to, or can be subjected to, force in a first radial direction. The second support element is arranged in a volume defined radially by the radial inner surface of the first slip ring, and the second support element is rotatably arranged relative to the first support element. Furthermore, the first contact pin can be subjected to force by a fluid on the side radially opposite the sliding contact. The invention further comprises a rotor of a separately excited synchronous machine.

The invention discloses an AGC information physical system reliability verification method and system, and relates to the technical field of power dispatching automation. The problems that an existing AGC system only adopts a static operation mode and an ideal communication condition in a simulation test, and coupling response of continuous operation and sudden disturbance of a power grid under a long time scale is difficult to reproduce truly are solved. The state evolution under event driving is realized by constructing three types of simulation event sources of a time sequence operation sample, a master station control instruction and external disturbance and setting a priority mechanism of external disturbance gt, master station instruction gt and time sequence propulsion; an uplink channel fault model is introduced to simulate on-off, delay and errors of measurement data, and a downlink channel fault model is introduced to simulate transmission abnormity of a control instruction; closed-loop simulation of frequency response and electrical quantity updating is realized by combining promotion of a rotor motion equation and dynamic load flow calculation; and finally, by analyzing indexes such as frequency deviation, tie line deviation and control response delay, comprehensive reliability evaluation of the AGC system in a complex information physical environment is completed.

The invention discloses a method for predicting the remaining service life of a control moment gyroscope based on parameter fusion, and relates to the technical field of health management of spacecraft attitude control systems. According to the method, optimal fusion of measurement parameters and implicit parameters is realized through adversarial learning feature extraction and a channel attention mechanism, and the method is particularly suitable for high-precision residual life prediction of the spacecraft control moment gyroscope under variable working conditions. The method comprises four main steps of data preparation and multi-source input, adversarial learning feature extraction, SE-Attention feature fusion and three-stage training optimization. In the data preparation step, original time sequences of voltage and current of a rotor motor are collected through a built-in electrical sensor of a CMG, and key physical parameters of a full-film lubrication friction coefficient, lubricating oil viscosity, a bearing clearance and contact stiffness are inverted based on an electromechanical coupling model; in the adversarial learning step, a game framework of a feature extractor and a working condition discriminator is constructed, and working condition-independent robust feature extraction is realized through a gradient inversion layer; in the SE-Attention feature fusion step, importance weights are adaptively distributed to different feature channels through an extrusion-excitation mechanism; and the three-stage training optimization step adopts a preheating-confrontation-fine tuning strategy to ensure the network convergence. The method solves the problem of domain adaptation, has the technical advantages of strong robustness, high precision, strong generalization, interpretability and self-adaptation, and can realize high-precision RUL prediction under variable working conditions.

A rotor (100) for an electric machine (170) is described. The rotor (100) comprises a hollow rotor shaft (110) of a first diameter (D1); a rotor core (140) attached to the hollow rotor shaft (110); a rotor insert (130) arranged in the rotor core (140) such that an annular gap (150) configured to guide a coolant is provided between an inside of the rotor core (140) and an outside of the rotor insert (130); and a first plurality of guiding ribs (210a), configured to guide a coolant flow of a coolant, flowing radially from the hollow rotor shaft (110), along a first axial ending (135a) of the rotor insert (130) to the annular gap (150) of a second diameter (D2), which second diameter (D2) is larger than the first diameter (D1). An electric machine (170) and a vehicle (500) are also described.

A second gear meshes with a first gear and is connected to an output member so as to rotate integrally with each other. A rotor, a planetary gear mechanism, and the first gear are disposed on a first axis in a described order from an axial first side toward an axial second side. A connecting member, a differential gear mechanism, and the second gear are disposed on a second axis parallel to the first axis in a described order from the axial first side toward the axial second side. The planetary gear mechanism has a smaller diameter than a rotating electric machine and a larger diameter than the first gear. The differential gear mechanism has a smaller diameter than the second gear and larger diameter than the connecting member.

A method is proposed for determining a zero-force reference position of a wet-running brush actuator (2) for external excitation of a rotor of an electric motor (EM) arranged on a rotor shaft (RW). While an electric vehicle with an electric motor (EM) is stationary and the rotor is externally excited, a spindle (10) of the brush holder (2), which has an electric stepper motor (4) with an integrated spindle drive, is moved away from the grinding brushes (B1, B2) until the contact between the grinding brushes (B1, B2) and the associated slip rings (SR1, SR2) reaches a contact quality limit, the position assumed by the spindle (10) being defined as the zero-force reference position, from which the steps of the stepper motor (4) are counted in order to variably press the grinding brushes (B1, B2) against the slip ring (SR1, SR2) as required. In addition, a computer program, a computer program product, a system, and an electric vehicle are proposed.

The invention discloses an unmanned aerial vehicle nest top cover dual-motor control method and device, and relates to the technical field of unmanned aerial vehicles, and the method comprises the steps: setting a system state variable and a control input vector based on nest top cover data, first motor drive data, second motor drive data, coaxial transmission data and top cover angle data; constructing a motor rotor kinetic equation based on corresponding data in combination with a shaft torsion effect; constructing an angle kinetic equation and an electrical kinetic equation of the nest roof based on the corresponding data; constructing a state space model based on a system state variable, a control input vector and the kinetic equation to generate LQR optimal control, integral control and coupling suppression control in combination with a current difference; and determining a comprehensive control model based on gravity feed-forward compensation in combination with LQR optimal control, integral control and coupling suppression control so as to control the double motors. According to the invention, global optimality and control stability are guaranteed, multi-target control is realized, and the control precision of double motors is significantly improved.

Aircraft capable of hovering comprising a fuselage at least one rotor that is rotatable with respect to the fuselage, electrical drive means adapted to rotate the rotor and electrically powered by a battery, and a cooling system of the battery. Said cooling system comprises, in turn, a first opening for the air to enter, second openings for the air to escape and a passage which places the first opening in fluidic communication with the second openings and within which the battery is placed. The cooling system further comprises a fan adapted to increase the kinetic energy of the air contained in the passage and which is operated when the forward speed of the aircraft with respect to the ground is lower than a speed threshold value and / or when the temperature of the battery exceeds a temperature threshold value.

An air turbine and a power generation device, the air turbine comprising a chamber, a valve and a rotor. The chamber comprises a first opening communicating with the atmosphere; the air pressure in the chamber is adjustable, and the difference between the air pressure in the chamber and the atmospheric pressure comprises a first air pressure difference and a second air pressure difference; the valve is connected with the chamber and is configured to open under the action of the first air pressure difference to form a first air flow by the chamber communicating with the atmosphere through the valve and the first opening respectively, and to close under the action of the second air pressure difference to form a second air flow by the chamber communicating with the atmosphere through the first opening, the directions of the first air pressure difference and the second air pressure difference being opposite; the rotor is configured to rotate under the drive of the second air flow. The air turbine can be used for power generation to convert the kinetic energy of the rotor into electrical energy, for example, the first air pressure difference and the second air pressure difference are obtained by utilizing the fluctuation of waves, and ultimately the wave energy is converted into electrical energy.

A slip ring arrangement according to the invention for an electric machine comprises a first slip ring module, comprising a first slip ring for electrical contact, a first conductor extending axially from the slip ring and electrically connected to the first slip ring, and a substantially hollow cylindrical first support element. The first slip ring is arranged on the support element in a first axial section on a radial outer surface. In a second axial section, the first conductor is enclosed by the first support element between a radial inner surface and a radial outer surface. Furthermore, a circumferential first web is arranged on the outer surface between the first axial section and the second axial section. The invention further comprises a rotor of a separately excited synchronous machine.

An energy dissipation system for a vehicle, the energy dissipation system comprising an air compressor comprising a compressor inlet configured to receive ambient air, an electric motor comprising a rotor having a rotor shaft operatively connected to a compressor shaft of the air compressor, power electronics arranged in a power electronics housing, the power electronics being electrically connected to the electric motor and configured to feed electric power to the electric motor, and an air flow channel through which the ambient air is configured to be fed to the compressor inlet, the air flow channel being formed by an inner elongated tube member and an outer elongated tube member, wherein the electric motor is housed within the inner elongated tube member and attached to a first inner surface, and wherein the power electronics housing is attached to a second outer surface.

A brake actuator (10) is specified, in particular for an electromechanical vehicle brake, having a brake caliper (12) in which an intermediate space (14) is formed for a brake rotor, wherein a brake pad (16), which can be applied against the brake rotor, is arranged in the intermediate space (14), a brake piston (18) for applying the brake pad (16) against the brake rotor, a spindle drive (20) which comprises a spindle (22) which is driven by an electric motor and a spindle nut (24) which is mounted on the spindle (22) via a thread pair which is designed to be self-releasing, and a ball ramp mechanism (28) which comprises a first ramp body (30) which is mounted fixedly in terms of rotation and which has an actuating surface (32) which is oriented toward the brake piston, and a second ramp body (34) which is arranged between the first ramp body (30) and the spindle nut (24). The spindle nut (24) is axially applied by means of a spring (35) against the second ramp body (34) and this second ramp body is axially applied against the first ramp body (30). The brake actuator (10) also comprises an electric motor which is coupled in terms of drive via a gear unit (26) to the spindle (22), in order to apply the brake piston (18) against the brake rotor (16).

A discharge device for discharging electric currents from a rotor part of a machine, said rotor part having a shaft, the discharge device comprising an axially displaceable contact element, which is at least partly accommodated in a guide, for forming an electroconductive sliding contact between a sliding contact surface of the contact element and a shaft contact surface of the shaft, the sliding contact surface being provided for forming the sliding contact, the contact element being electroconductively connected to the guide and / or a retaining element of the machine, and the contact element being prestressed towards the shaft contact surface by means of a spring element, the contact element being at least partly wetted with an oily fluid, in particular at least in the area of its sliding contact surface.

A propulsion system is provided for an aircraft. This propulsion system includes a propulsor rotor, a drivetrain, a first power unit and a second power unit. The drivetrain is coupled to the propulsor rotor. The first power unit includes a first overrunning clutch and a first electric motor. The first overrunning clutch is configured to selectively couple the first electric motor to the drivetrain. The first electric motor is configured to drive rotation of the propulsor rotor through the first overrunning clutch and the drivetrain. The second power unit includes a second overrunning clutch and a second electric motor. The second overrunning clutch is configured to selectively couple the second electric motor to the drivetrain. The second electric motor is configured to drive the rotation of the propulsor rotor through the second overrunning clutch and the drivetrain.

One aspect of a rotor core of the present invention is a rotor core of a rotor rotatable around a central axis, the rotor core including a pair of first magnet holes adjacent to each other in a circumferential direction, and a first hole portion located between a pair of the first magnet holes in the circumferential direction. A pair of the first magnet holes extend in directions away from each other in the circumferential direction from the inner side in a radial direction toward the outer side in the radial direction when viewed in an axial direction. The first hole portion is provided at a position overlapping a first virtual line passing through the center in the circumferential direction between a pair of the first magnet holes and extending in the radial direction when viewed in the axial direction, and has an asymmetric shape across the first virtual line.

The distance formed between surfaces facing in the thickness direction of the permanent magnet is set to be larger than the thickness of the permanent magnet, whereby gaps are formed between the permanent magnet and the magnet insertion holes. The magnet insertion hole of the first rotor core has formed therein a guide portion for positioning the permanent magnet. The magnet insertion hole of the second rotor core has formed therein an opening portion that connects the gap and the flux barrier to each other. The first rotor core and the second rotor core are laminated together in a mixed manner in the axis direction.

Systems are provided for a rotor shaft assembly for an electric machine. A rotor shaft assembly includes a shaft, a shaft end cap, and a flow insert arranged in a cavity shaped by the shaft and the shaft end cap. The flow insert comprises an inner core formed of a first material; and an outer shell formed of a second material different from the first material, where the outer shell is overmolded over the inner core, and where the outer shell comprises flow channels.

An aircraft system is provided that includes a propulsor rotor, an electric machine and a gas turbine engine. The electric machine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine includes a compressor section, a combustor section, a turbine section, an exhaust duct and a flowpath extending through the compressor section, the combustor section, the turbine section and the exhaust duct. The exhaust duct extends longitudinally along the electric machine. The exhaust duct extends partially circumferentially about the electric machine between opposing circumferential sides of the exhaust duct.

The utility model discloses an impact block and rotor pressing device for electric hand drill production, which comprises a bearing, the two supporting columns are fixedly arranged at the top of the workbench in a bilateral symmetry mode, the transverse plate is fixedly arranged between the tops of the two supporting columns, and the four vertical rods are fixedly arranged at the top of the workbench in a front-back symmetry mode and located on the outer side of the transverse plate. The transverse plate is arranged on the top of the workbench, the sliding pushing assembly is arranged on the top of the workbench in a sliding mode and located on the lower side of the transverse plate, the placing plate is arranged on the sliding pushing assembly and located on the upper side of the transverse plate, the positioning inserting cylinder is fixedly arranged on the top of the transverse plate and located on the right side of the placing plate, and an impact block body can be placed on the placing plate. And a rotor body can be inserted into the positioning insertion hole.

The utility model relates to the field of motor component detection, and discloses a low-vibration motor rotor dynamic balance detection mechanism which comprises a base, a transmission mechanism is arranged on the base, and a pressure adjusting mechanism is arranged on the transmission mechanism. The pressure adjusting mechanism comprises a mounting plate, a moving frame, an electric push rod, a connecting plate, a moving block, a roller, a pressure sensor and a plurality of limiting rods, the moving frame is fixedly mounted at the bottom end of the mounting plate, and the electric push rod is fixedly mounted on the mounting plate and extends into the moving frame; according to the utility model, the pressure adjusting mechanism is arranged, the mounting plate is mounted on the second connecting rod, and the electric push rod and the moving frame are mounted on the mounting plate, so that when the transmission belt presses the outer wall of the rotor, the moving block retracts under pressure, one end of the pressure sensor presses the connecting plate, and detection is carried out through the pressure sensor; the pressure borne by the inner ring of the transmission belt can be detected, the contact force between the transmission belt and the rotor can be adjusted more visually, and proofreading is more convenient.

The invention relates to the technical field of electric wheelchair control, and discloses an automatic power-assisted control method, system and equipment for an electric wheelchair, and the method comprises the steps: responding to a power-assisted starting instruction sent by a power-assisted switch module, and obtaining the back electromotive force of a motor and the position information of a motor rotor; according to the back electromotive force of the motor and the position information of the motor rotor, the thrust direction of the electric wheelchair is determined; the actual output power of the motor is obtained, the actual output power of the motor is adjusted by combining the thrust direction of the electric wheelchair and the counter electromotive force of the motor, and the preset assistance strength requirement is met. Power is started through the power-assisted switch module, the thrust direction is judged by combining the positions of the motor and the motor rotor, high-price sensors for torque, angle and the like do not need to be additionally arranged, the control structure is simplified, the cost is reduced, and the actual output power is dynamically adjusted by obtaining the actual output power of the motor and combining the thrust direction and the counter electromotive force of the motor.

An unmanned aerial vehicle (UAV) configured for autonomous operation includes an electric propulsion system comprising a plurality of motors and a plurality of rotors and a sensor system. A control system receives data from the sensor system for controlling the electric propulsion system. A battery system includes a plurality of battery cells and a charging system for receiving power a by electro-magnetic induction from a power line cable. The UAV is for inspection of AC-overhead power lines. A method includes operating the UAV comprising generating image data relating to an overhead power line by the sensor system, approaching a power line cable by the UAV, receiving power from the power line cable by the charging system and charging the battery with the power received, and the UAV taking off from the cable.

A vibration mechanism for a concrete finishing tool includes adapters for removable attachment to the tool and a device housing with a general chamber supporting a battery electrically connected to a vibrator assembly, which includes a vibrator housing with annular fins and openings that slow heat transfer and direct heat away from other components. Vibrator assembly components positioned in vibrator housing are a rotor with a rotor shaft and weighted body, a bearing supporting the rotor, a motor with an output shaft, a combination spacer with a resilient spacer band and a micro motor shaft seal positioned adjacent the motor and around the motor output shaft, and a resilient link between the rotor shaft and the motor output shaft. A resilient vibrator band around the vibrator housing transfers vibrations to the device housing and together with the combination spacer minimizes fluid leakage within the vibrator assembly and device housing.