41 results about "Gyroscopic moment" patented technology

The invention belongs to the technical field of wind tunnel tests, and particularly relates to a precession simulation device for a spiral flutter wind tunnel test. According to the invention, the design problem of the rotor craft spiral flutter wind tunnel test device is solved, and the key influence parameters and influence rules of the spiral flutter of the aircraft are researched by designing the precession motion simulation device of the rotor craft. Rotation of the rotor wings can be realized in the wind tunnel, and the rotating speed of the rotor wings is adjusted through the motor. Meanwhile, pitching and deflection modal decoupling of the rotating shaft of the rotating system is achieved, and pitching and deflection modal frequencies are independently adjustable; meanwhile, the axis of the pitch axis and the axis of the yaw axis coincide, so that pitching and yaw freedom degree coupling precession motion can be achieved under the effect of gyroscopic moment. Meanwhile, nacelle rotating mass rotational inertia, nacelle weight and mass center position adjustment can be achieved; and finally, the rotating speed of the rotating mass such as the rotor wing and the propeller hub can be adjusted through a speed adjusting motor, matching of the rotating speed and the incoming flow speed is guaranteed, and the spiral flutter state is achieved.

An automobile hub bearing comprises a hub bearing body and an inflation device, the hub bearing body is composed of an inner ring (1), an outer ring (2), a main shaft (3), a steel ball (4), a retainer (5), a wheel side sealing ring (6) and an automobile body side sealing ring (7), and the outer ring (2) comprises an air channel with an air inlet (21). The inflating device comprises a ventilation pipe column (11) and a sealing component, the ventilation pipe column (11) penetrates through a disc-shaped flange (31) of the main shaft (3) and is connected with the disc-shaped flange (31) in a sealing mode, and the sealing component is used for keeping the space between the inner side end of the outer ring and the disc-shaped flange sealed. The sealing component comprises an outer ring inner diameter inner side sealing mechanism and an outer ring outer diameter sealing mechanism. The outer ring inner diameter inner side sealing mechanism is a wheel side sealing ring of the hub bearing. The automobile hub bearing is simple in mechanical structure, low in manufacturing cost and high in machining realizability, and the necessary waterproofness, airtightness and gyroscopic moment of the whole device can be guaranteed.

The embodiment of the invention provides a wind turbine generator control method and device, electronic equipment and a floating type double-machine-head wind turbine generator, and relates to the technical field of wind power. The method comprises the steps that the horizontal yaw angle speed of each cabin is obtained based on each gyroscope, and the equivalent floating body total yaw angle speed is obtained based on each horizontal yaw angle speed; and according to the equivalent floating body total yaw angular velocity, the equivalent yaw angular velocity corresponding to the rotation axis of each impeller is determined. And on the basis of a preset pitching gyroscopic moment calculation formula, determining a pitching gyroscopic moment value generated by each machine head according to each equivalent yaw angular velocity. And respectively controlling the pitch variation of the corresponding machine head based on the pitch gyro moment value corresponding to each machine head. The operation stability of the wind turbine generator can be improved.

The present invention provides a balancing system and a two-wheeled vehicle having the same, wherein the balancing system is used to control the swing of a moment gyro to maintain the balance of the two-wheeled vehicle, and the balancing system comprises: a fixed frame; a moment gyro, the moment gyro is pivotally arranged on the fixed frame; a driving device, the driving device is connected to the moment gyro, and the driving device comprises: a power output part, the power output part is arranged on the fixed frame; a screw rod, the screw rod is drivingly connected to the power output part; a connecting structure, the connecting structure is connected to the moment gyro, and the connecting structure is threadedly connected to the screw rod, so as to reciprocate along the screw rod under the drive of the screw rod to drive the moment gyro to swing. The present invention solves the problem that the mechanism of driving the moment gyro to swing of the two-wheeled vehicle in the prior art is simple and cannot provide sufficient torque for the moment gyro, so that when the flywheel speed of the moment gyro is too high, the moment gyro cannot be reliably guaranteed to swing, thereby causing the two-wheeled vehicle to lose balance.

The invention discloses a fixed-wing unmanned aerial vehicle flight control method based on active disturbance rejection control, and belongs to the technical field of fixed-wing unmanned aerial vehicle flight control. The problem that the attitude control performance is poor due to the fact that aerodynamic interference of the propeller is not considered in an existing method is solved. According to the method, aerodynamic interference factors of propellers are systematically introduced into modeling and control design, namely, reaction torque and gyroscopic moment are introduced into the modeling and control design, and a flight control system of the fixed-wing unmanned aerial vehicle is designed based on an active disturbance rejection control strategy; and dynamic and external disturbances which are not covered by the model are estimated and compensated in real time, so that the attitude control performance of the fixed-wing unmanned aerial vehicle is improved. Meanwhile, under various given input signals, simulation verification is performed on the performance of the active-disturbance-rejection controller designed by the invention, which shows that the performance of the active-disturbance-rejection controller designed by the invention can meet design indexes. The method can be applied to flight control of the fixed-wing unmanned aerial vehicle.

The invention discloses an aero-engine global attitude-gyroscopic moment composite test system, and relates to the technical field of aero-engine tests. The technical problems that an existing test system cannot achieve precise coupling simulation of global attitude coverage and gyroscopic moment, the test precision is low, and the scene is single are solved. The system comprises a multi-axis linkage attitude simulation platform, a high-precision gyroscopic moment loading system, a linear load loading system and a wheel rail support system. The multi-axis linkage attitude simulation platform can realize aeroengine global attitude adjustment, and the high-precision gyroscopic moment loading system dynamically outputs a matched gyroscopic moment based on real-time attitude data. According to the method, the attitude change and gyroscopic moment coupling effect of the aero-engine under the complex flight working condition can be truly reproduced, the test authenticity and data reliability are remarkably improved, and key technical support is provided for design optimization and performance verification of the aero-engine.

The invention discloses a ball screw contact characteristic calculation method and system, and the method comprises the steps: inputting a size parameter and an external load of a ball screw, and preliminarily building a related equation of a ball stress and an axial load; solving the displacement change of the raceway contact point under the action of the axial load according to the balance condition of the binding force; adding rotating speed parameters of the ball screw, calculating position offset of a raceway contact point during high-speed rotation, and updating a contact angle between the ball and the screw / nut; the centrifugal force and gyroscopic moment generated by high-speed rotation of the ball are quantified through a geometric constraint equation and kinematics analysis; on the basis of an original static model, centrifugal force, gyroscopic effect and contact surface friction force are superposed, and axial and radial stress balance equations containing dynamic factors are reconstructed; and a geometric constraint equation and a multi-dimensional mechanical equation are combined, numerical calculation is carried out by adopting a Newton iteration method, and finally, the contact characteristic which not only considers uneven load distribution but also contains the influence of high-speed rotation is obtained.

The application discloses a kind of anti-swing assemblies based on double control moment gyroscopes, including shell, controller, attitude sensor, two double control moment gyroscopic components and two joints, shell is vertically arranged cylindrical piece, two joints are respectively arranged inside the both ends of shell, two double control moment gyroscopic components are arranged in two shells, and located between two joints, attitude sensor is arranged in the middle of lower joint, two joints are respectively used to be connected with outside setting, the gyroscopic moment direction of two double control moment gyroscopic components is mutually perpendicular in horizontal direction, controller is arranged in shell, and attitude sensor and two double control moment gyroscopic components are electrically connected with controller, two double control moment gyroscopic components are used to reduce the swing amplitude of shell, the anti-swing assembly based on double control moment gyroscopes can be applied by X direction and Y direction gyroscopic moment of two double control moment gyroscopic components in it respectively to make the swing amplitude of whole detection equipment reduce to keep stable.

The application discloses a large-length-diameter-ratio rotor structure with a separated turbine, comprising a four-stage fan, a two-stage front turbine, a single-stage rear turbine, four bearing supporting points, a connecting structure and the like. A 1-2-1 four supporting point supporting scheme is adopted, and an intermediate supporting point is additionally arranged at the front turbine to control the bending deformation of the large-length-diameter-ratio rotor. Meanwhile, the two-stage front turbine in the middle section of the rotor is designed as an integrated ring cavity structure, the structure angular rigidity is enhanced, and the overall gyroscopic moment effect is exerted. The front turbine and the rear turbine are connected with the rotor shaft through a large-space double-centering-face stop mouth-toothed sleeve connection, the bending moment bearing capacity is improved, the gyroscopic moment of the wheel disc is fully applied to the shaft section, the rotor resonance speed safety margin is improved, and the bending deformation is controlled. The application is the first rotor structure proposed for a new engine with an inter-stage combustion chamber, and meets the dynamic design requirements of the rotor with the characteristics of the multi-stage separated turbine and the large-length-diameter ratio.

To provide a saddle type monorail system obtaining double track and unmanned operation which is monorail replacing single track railroad with few users and using the existent railroad tracks as it is.SOLUTION: Monorail is run on one side rail of a railroad track by a rolling prevention means using a gyro moment generation mechanism. A single pair of narrow gauge (generally 1067 mm) tracks are used as double track for up / down by a small vehicle. Unmanned operation is facilitated by simplifying to an operation circulating between both ends like in a ropeway with no vehicle evacuation when passing. In addition, combination operation with the conventional railroad vehicle is possible by leaving the railroad tracks. Thus, it becomes a transportation means that allows easy adjustment of transportation capacity to such as time variation or seasonal variation in student passenger transportation and population variation.SELECTED DRAWING: Figure 1

The invention belongs to the field of engine design, and particularly relates to an aero-engine whole machine dynamic structure design parameter optimization method, which utilizes an APDL language of ANSYS software to carry out parametric modeling on an aero-engine whole machine (including a rotor, a support and a stator casing), and applies additional centrifugal force and additional gyroscopic moment generated by maneuvering flight. The stress level of the bearing case, the strain energy distribution of a rotor system and the rotor and stator gap change are obtained through bearing case stress analysis, critical speed analysis and unbalanced response analysis. Based on the analysis results, multi-objective optimization is carried out on complete machine dynamic design parameters, so that the stress level of a force bearing casing is lowest, rotor strain energy distribution meets rotor dynamic design requirements, rotor and stator gap changes are minimum, the rub-impact risk is reduced, optimization of the structural design parameters is completed through software, the design efficiency is improved, and the design cost is reduced. The design period is shortened.

This application discloses an online identification method, apparatus, aircraft, and computer-readable storage medium for aircraft parameters, relating to the field of aircraft technology. The method includes: acquiring first parameters of the aircraft under low-frequency control commands; iteratively calculating an optimization function based on the first parameters to obtain a control efficiency optimization matrix; updating the optimization function based on the control efficiency optimization matrix; acquiring second parameters of the aircraft under variable-frequency control commands; iteratively calculating the updated optimization function based on the second parameters to obtain a gyroscopic torque optimization matrix and a transfer function optimization matrix; and determining a target control efficiency matrix, a target gyroscopic torque matrix, and a target transfer function matrix based on the control efficiency optimization matrix, the gyroscopic torque optimization matrix, and the transfer function optimization matrix. This application enables online identification of aircraft characteristic parameters through optimization functions, improving the convenience of aircraft parameter identification and allowing the aircraft to achieve optimal flight performance under different operating conditions.

To provide a compact and easy-to-use azimuth detection method, azimuth detection device, and surveying device. [Solution] The system includes a sensor unit 7 that detects tilt and rotation relative to the horizontal, and a flywheel 18 provided on the sensor unit that has a rotation axis extending in the vertical direction. The flywheel is rotated at a constant speed, and the flywheel is tilted to generate a gyroscopic moment in order to counteract the change in tilt that occurs in accordance with the rotation of the Earth, and the direction of the Earth's axis (north or south) can be determined from the direction of the gyroscopic moment.

The application discloses a kind of based on digital twin model driven intelligent spindle micro-amplitude vibration control method and system, method specifically is: based on intelligent spindle physical entity characteristic parameter and operating condition, establishes intelligent spindle digital twin model;Based on spindle digital twin model, the mapping relationship between rotor unbalance centrifugal force, gyroscopic moment and bearing gap and spindle / shell vibration response is established;Based on intelligent spindle micro-amplitude vibration response, consider the intelligent spindle-milling-actuating closed-loop system of coupling action of spindle milling force and control force;Intelligent spindle vibration signal is input to controller, and control voltage is exported according to objective function and constraint condition, and control voltage signal is amplified after being input to piezoelectric actuator, and drive it to exert active control force to intelligent spindle system, to suppress the micro-amplitude vibration of spindle;The present application considers the comprehensive influence of spindle milling force and actuator control force on spindle vibration response, and realizes spindle micro-amplitude vibration suppression.

Embodiments of the present invention provide a wind turbine control method, device, electronic equipment, and a floating dual-head wind turbine, relating to the field of wind power technology. The method comprises: obtaining the horizontal yaw angular velocity of each nacelle based on each gyroscope, and obtaining the equivalent total yaw angular velocity of the floating body based on each horizontal yaw angular velocity. Determine the equivalent yaw angular velocity corresponding to the rotation axis of each impeller based on the equivalent total yaw angular velocity of the floating body. Based on a preset pitch gyro moment calculation formula, determine the pitch gyro moment value generated by each head according to each equivalent yaw angular velocity. Control the corresponding head pitch change based on the pitch gyro moment value corresponding to each head. The present invention can improve the stability of wind turbine operation.

The invention discloses a dynamic modeling method for a variable-centroid unmanned aerial vehicle, and belongs to the field of unmanned aerial vehicle dynamic modeling. The method comprises the steps that a ground coordinate system and a vehicle body coordinate system are established; defining a system configuration comprising a machine body part, a pitching channel mobile battery and a rolling channel mobile battery; calculating a system centroid position; establishing a system translation dynamic model; establishing a system rotation dynamical model considering an additional inertia moment, an additional Coriolis moment and an additional gyroscopic moment; establishing a dynamic model of the mobile battery; and a complete eight-degree-of-freedom nonlinear dynamic model is formed. According to the method, the battery of the unmanned aerial vehicle serves as a moving mass block, the complex dynamic phenomenon and the strong coupling relation generated in the battery moving process are accurately described, compared with the prior art, the system complexity and cost are remarkably reduced, and a reliable theoretical basis is provided for design of a variable-centroid unmanned aerial vehicle control system.

The invention discloses a bucket-wheel reclaimer cantilever gyroscopic moment protection method and system based on intelligent monitoring, and relates to the technical field of moment data processing. The bucket-wheel reclaimer cantilever gyroscopic moment protection method and system based on intelligent monitoring comprise the steps that S1, cantilever gyroscopic working condition data are periodically collected, and the cantilever gyroscopic working condition data are preprocessed; s2, calculating a cantilever rotation moment value, performing sliding window division by taking a sampling period as a unit, evaluating the stability of a cantilever rotation working condition, and marking an abnormal window; s3, evaluating the abnormal strength under the cantilever rotation working condition, judging the operation risk level in the current abnormal window, and triggering a hierarchical protection strategy; and S4, the recovery trend of the cantilever rotation working condition is evaluated, and the protection strategy is dynamically adjusted. The problem that in the prior art, due to the fact that a bucket-wheel material taking machine cantilever is difficult to recognize local resistance mutation in time in the rotation process, cantilever rotation moment anomaly detection lags behind is solved.

According to the medium-low speed maglev vehicle and the transverse stabilizing device thereof, when the maglev vehicle passes through a curve road section, shaking of a vehicle body is inhibited by providing a gyroscopic moment, a pin shaft is used as a rotation center, a cantilever beam is used as a force arm, and a shock absorber is used as force input. The stress of the shock absorber can be reduced by increasing the length of the cantilever beam. When the maglev vehicle shakes the head, the vehicle body and the suspension frame move relatively, the movable sliding table at the end moves to sequentially drive the screw assembly, the rotating arm, the pin shaft and the cantilever beam to rotate, at the moment, one of the two shock absorbers is pulled, the other shock absorber is pressed, torque in the same direction is provided, the rotating arm is promoted to return to the initial position, and the vibration of the maglev vehicle is reduced. Therefore, the head shaking motion of the magnetic levitation vehicle is inhibited. By means of the arrangement, on the basis that functionality is guaranteed, the transverse stabilizing device of the medium-low-speed magnetic levitation vehicle has good buffering and vibration reduction performance when facing transverse disturbance, and the influence on the curve passing performance of the magnetic levitation vehicle can be effectively reduced.

The present invention provides a high-intensity flight robot heat dissipation structure that combines heat dissipation and flight aerodynamics, and belongs to the field of aircraft heat dissipation structures. In order to solve the problem that the additional airflow generated by the existing air-cooled heat dissipation device is easy to form coupling interference with the main flight airflow, resulting in degradation of aerodynamic characteristics. The present invention includes a flight control circuit board heat dissipation structure located at the center of gravity of the robot, a Jetson Orin NX heat dissipation structure, a binocular camera heat dissipation structure symmetrical on the front and rear sides, and a TOF obstacle avoidance module heat dissipation structure, which are used to achieve robot heat dissipation without generating torque and gyroscopic torque that affect the robot's posture. The present invention ensures the robot's motion control stability while ensuring heat dissipation performance, can effectively protect important components, extend the robot's service life, improve the robot's operating stability and safety, and ensure the robot's motion control stability, providing technical support for the performance improvement and practical application of high-intensity flight robots.

The invention relates to the technical field of mobile two-wheeled self-balancing vehicle motion control, and discloses a two-wheeled vehicle omnidirectional maneuvering chassis platform based on self-balancing control and a control system thereof, and the omnidirectional maneuvering chassis platform comprises a chassis, a control moment gyroscope and an angle adjusting mechanism; a control system; the state of the gyroscope is monitored through the sensing module, dynamic mapping of the gyroscope saturation and the mechanical deformation range is established through the safety constraint module, and the maximum outward-splayed field angle boundary allowed by the moving wheel is calculated in real time. The motion planning module adopts a frequency domain layering decoupling strategy, low-frequency disturbance is converted into a vehicle body side deviation instruction to be compensated by gravitational potential energy, and high-frequency disturbance is responded by gyroscopic moment. And the cooperative execution module superposes a micro-flutter signal to reduce the ground friction resistance when the variable structure is in high load. Through the coupling control of momentum management and the variable structure boundary, the problems of gyroscope angular momentum saturation failure and instability in the variable structure process are effectively solved, and the maneuvering stability of the chassis is improved.

This invention discloses a dynamic modeling method for a variable center of mass unmanned aerial vehicle (UAV), belonging to the field of UAV dynamic modeling. The method includes: establishing a ground coordinate system and a body coordinate system; defining a system configuration including the body, a pitch channel moving battery, and a roll channel moving battery; calculating the system's center of mass position; establishing a system translational dynamic model; establishing a system rotational dynamic model considering additional inertial torque, additional Coriolis torque, and additional gyroscopic torque; establishing a moving battery dynamic model; and forming a complete eight-degree-of-freedom nonlinear dynamic model. This invention uses the UAV's own battery as a moving mass block, accurately describing the complex dynamic phenomena and strong coupling relationships generated during battery movement. Compared with existing technologies, it significantly reduces system complexity and cost, providing a reliable theoretical basis for the design of variable center-of-mass UAV control systems.

The application provides a high-speed ball bearing dynamic characteristic analysis method considering raceway deformation, and belongs to the technical field of bearing dynamics. The method needs to determine basic parameters such as bearing geometric parameters, material properties and operation conditions, and establishes a high-speed angular contact ball bearing dynamics model under positioning and pre-tightening based on the Hertz contact theory and by comprehensively considering the influences of centrifugal force, pre-tightening force, raceway thermal deformation and gyroscopic moment of the bearing. Then, the influences of the bearing pre-tightening force and rotating speed on the bearing dynamic characteristic parameters under different working conditions are solved by the Newton iteration method, and the relationship between the pre-tightening force, rotating speed and bearing contact angle, contact load, centrifugal force and other parameters is obtained. The method has the characteristics that the influences of thermal effect and centrifugal effect on the bearing are considered, the bearing contact angle and contact load under different cutting conditions can be accurately calculated, and the method can provide a reference for the design and use of the motorized spindle bearing.

The utility model belongs to the field of clamping devices, and particularly relates to a rapid positioning clamp for liquid floated gyro torquer magnetic steel wire cutting, which comprises a block-shaped base, a guide rail seat, a guide rail sliding block, a threaded positioning rod, a positioning block and an external clamping positioning block, and is characterized in that the side surface of the base is provided with a trapezoidal boss; the guide rail base comprises a bottom supporting block, a top T-shaped block and a top abutting block, a trapezoid groove is formed in the side face of the bottom supporting block and matched with the trapezoid boss of the base, the top T-shaped block and the top abutting block are connected to the upper portion of the bottom supporting block, the top T-shaped block is connected with the top abutting block, and the top abutting block is higher than the top T-shaped block. The base and the guide rail seat are positioned through the trapezoidal grooves, positioning is accurate and reliable, the effect of fast reloading inside and outside a machine can be achieved, reloading efficiency is high, a side face clamping mode is adopted for machined parts, and the problem that workblanks warp up due to the fact that the upward pressing portion is too small is solved.

This invention belongs to the field of tiltrotor aircraft drive mechanism design, and discloses a tilt mechanism, a tiltrotor aircraft, and a method. This method determines key design input parameters of the rotor system, such as weight, moment of inertia, and tilt angular velocity. A rotary crank-guide rod mechanism is selected as the core transmission mechanism. A geometrical mathematical model of the tilt angle and linear servo travel is established to solve for the mechanism link length, theoretical travel, and minimum effective lever arm. Based on the input parameters, the total driving torque is obtained by superimposing inertial torque, gravitational eccentric torque, gyroscopic torque, and roll torque. Finally, the thrust requirement of the linear servo is calculated by combining the minimum effective lever arm and safety factor to complete the selection. This method achieves smooth and precise control, eliminating transmission jamming and uneven force distribution; it comprehensively considers the dynamic load during flight mode transitions, preventing flight control failure risks and increased structural redundancy and weight; and it improves design efficiency, matching accuracy, and overall mechanism reliability.

The present application belongs to the technical field of wind tunnel test, and particularly relates to a precession simulation device for a helical flutter wind tunnel test. The present application solves the problem of designing a helical flutter wind tunnel test device for a rotorcraft, and studies key influencing parameters and influencing rules of the helical flutter of the rotorcraft by designing a precession motion simulation device for the rotorcraft. The present application can realize the rotation of the rotor in the wind tunnel, and adjust the rotation speed of the rotor through a motor. Meanwhile, the precession system realizes the decoupling of the pitch and yaw modes of the rotation shaft, and the pitch and yaw mode frequencies are independently adjustable. Meanwhile, the axes of the pitch and yaw axes coincide, so that the precession motion of the pitch and yaw degrees of freedom can be realized under the action of the gyroscopic moment. Meanwhile, the adjustment of the rotation inertia of the nacelle rotating mass, the weight and the center of mass of the nacelle can be realized. Finally, the rotation speed of the rotating mass such as the rotor and the hub can be adjusted through the speed regulation motor, so as to ensure the matching of the rotation speed and the incoming flow speed, and achieve the helical flutter state.

The invention provides a high-intensive flying robot heat dissipation structure with heat dissipation and flight aerodynamic performance, and belongs to the field of aircraft heat dissipation structures. The problem that additional airflow generated by an existing air cooling heat dissipation device is prone to forming coupling interference with flying main airflow, and consequently aerodynamic characteristics are degraded is solved. The heat dissipation system comprises a flight control circuit board heat dissipation structure located at the gravity center of the robot, a Jetson Orin NX heat dissipation structure, binocular camera heat dissipation structures which are symmetrical on the front side and the rear side and a TOF obstacle avoidance module heat dissipation structure, and is used for achieving heat dissipation of the robot without generating moment and gyroscopic moment to affect the posture of the robot. The motion control stability of the robot is ensured while the heat dissipation performance is ensured, and the effects of effectively protecting important elements, prolonging the service life of the robot, improving the running stability and safety of the robot and ensuring the motion control stability of the robot can be achieved; and technical support is provided for performance improvement and practical application of the highly-intensive flying robot.

This invention provides a multi-degree-of-freedom aerodynamic load simulation device and its testing method for floating wind turbines, including a nacelle, an aerodynamic load generation module, an aerodynamic load control module, and a gyroscopic torque generation module. The load generation unit of the aerodynamic load generation module is mounted outside the nacelle via a support arm, and is used to generate aerodynamic loads along the length and width directions of the nacelle. The gyroscopic torque generation module includes a motor and a mass rod mounted on the nacelle; the motor drives the mass rod to rotate, generating a moment of inertia. The aerodynamic load control module controls the magnitude of the generated aerodynamic loads. This invention eliminates the need for complex and expensive physical wind fields, enabling accurate simulation of multi-degree-of-freedom aerodynamic loads on floating wind turbines under various operating conditions. It eliminates dependence on physical wind fields and model blades, solving the problems of needing to readjust the load application direction for different wind directions and the difficulty in accurately simulating complex loads under extreme and fault conditions.

The utility model belongs to the field of ball bearings, and particularly relates to a full complement mixed ceramic angular contact ball bearing, which comprises an inner ring, an outer ring and ball rollers, the ball rollers are ceramic rollers, a plurality of the ball rollers are fully complemented and assembled between an inner ring channel and an outer ring channel, the inner diameter surface of the outer ring is provided with a slope type ball locking port along the axial direction, and the inner diameter surface of the outer ring is provided with a slope type ball locking port. And the curvature radius of the inner ring channel is greater than that of the outer ring channel. According to the full-complement mixed ceramic angular contact ball bearing disclosed by the utility model, steel balls are replaced by the ceramic balls, so that not only is the weight of a complete set of bearing reduced, but also the gyroscopic moment generated by high-speed spinning of the steel balls is reduced, the sliding friction between the spinning of the steel balls and a raceway is reduced, the power consumption is reduced, the generated heat is small, and the quality is more stable. The proper locking amount of the bearing ring is increased, so that ball falling caused by ring expansion due to temperature rise during high-speed rotation is avoided.

This invention discloses an active intelligent multi-directional gyro stabilizer and its intelligent control algorithm for improving the flutter stability of long-span bridges. The gyro stabilizer structure includes a motor, an attitude angle sensor, a power supply box, a control box, a gyro stabilizer body, and a chain drive device. The gyro stabilizer obtains the aerodynamic torque at a unit torsional angle of the main beam by identifying the flutter derivative through wind tunnel testing. When the main beam undergoes torsion, the system combines the aerodynamic torque at the corresponding torsional angle of the main beam with the instantaneous optimal mapping relationship between the torsional angle of the main beam and the spin angular velocity of the gyro stabilizer established based on artificial intelligence neural network technology. It then outputs the spin angular velocity of the gyro stabilizer at the corresponding torsional angle of the main beam, as well as the gyro precession angular velocity calculated according to gyro precession theory. The chain drive device then controls the gyro precession to generate gyro torque, intelligently controlling the motion state and attitude behavior of the stabilizer, thereby improving the flutter stability of the bridge cross-section.

The invention belongs to the field of motors, and relates to a flywheel energy storage device. The device comprises an outer shell, a first rotating shaft is rotationally installed in the outer shell, a replacing assembly is installed on the first rotating shaft, the section of the first rotating shaft is sleeved with a first flywheel, a second rotating shaft is arranged above the first rotating shaft, the position, close to the bottom end, of the second rotating shaft is fixedly sleeved with a second flywheel, and a third flywheel is arranged at the bottom of the second flywheel. A flywheel set is formed by combining a flywheel III and a flywheel II, a connecting shaft is fixedly connected to the bottom of the flywheel III, an auxiliary assembly is installed on a rotating shaft II and the connecting shaft, a cooling assembly is installed outside the outer shell, and two flywheel rotors with the same structural parameters are coaxially arranged and synchronously rotate in the opposite directions, so that the gyroscopic moments of each other are effectively counteracted; the running stability in a dynamic environment is improved, the shell does not need to be disassembled for maintenance, the downtime is shortened, the damaged flywheel is rapidly replaced and adjusted, and the service life of key components is prolonged.