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73results about How to "Realize full closed-loop control" patented technology

3D (three-dimensional) printing system structure

InactiveCN103831975AGuaranteed uptimeReduced motor modulationOptical axisDrive shaft
The invention relates to a 3D (three-dimensional) printing system structure. The 3D (three-dimensional) printing system structure comprises a lifting printing platform, a dual-screw dual-optical-axis Z-shaft driving mechanism, an X-shaft drive mechanism, a Y-shaft drive mechanism as well as a stationary object carrying platform, wherein the printing platform is provided with an X-shaft drive motor and a Y-shaft drive motor; the two motors are respectively connected to a pair of driven bearings by synchronous belts at two ends of the driving shaft; double slide shafts in the X direction and the Y direction are both provided with slide seats; two pairs of slide seats are respectively connected by an X cross beam and a Y cross beam, and the two cross beams respectively penetrate through a 3D printer head; a driving motor of the dual-screw dual-optical-axis driving mechanism and the driving shaft are connected by the synchronous belt; the position of the driving motor can be adjusted randomly. The X-shaft drive mechanism, the Y-shaft drive mechanism and the driving shaft operate individually, so that the motion modulation is reduced; the dual-screw dual-optical-axis driving mechanism has favorable stability, so that the printing platform is stressed in a balance manner; the driving in each direction is stable; the 3D printing precision is improved.
Owner:UNIV OF SCI & TECH OF CHINA

Synergetic control method of aircraft part pose alignment based on four locater

The invention discloses a method for adjusting and synergetically controlling the position and pose of an aircraft component based on four locators. The method comprises the following steps: firstly, a global coordinate system OXYZ is established, and the current position and pose and the target position and pose of the aircraft component are calculated under the global coordinate system; secondly, the automatic adjusting path and the inch adjusting path of the aircraft component are formed; thirdly, the track of the sphere pivot wiring point between the locator and the aircraft component is planed according to the automatic adjusting path and the inch adjusting path; fourthly, the track of the sphere pivot wiring point is inverted into the driving parameter of a 12 motor axle synchronous control network; fifthly, the 12 motor axle synchronous control network is built based on a SynqNet bus, and the position servo of single motor axle adopts the full-closed loop digit controlling; and sixthly, two locators are selected, and the collocated relation between the locators is the master-slave motion mode. The method has the following advantages: firstly, the path for adjusting the position and pose of the aircraft component can be planed; secondly, the full-closed loop controlling of the single axle motion of the locator can be realized; and thirdly, the 12 axle synchronous motion of the position and pose adjusting system can be realized.
Owner:ZHEJIANG UNIV +1

Planar parallel mechanism end tracking control system based on two-dimensional encoder and planar parallel mechanism end tracking control method thereof

ActiveCN106054806AImprove positioning accuracy and tracking accuracyGood real-time performanceProgramme controlComputer controlEmbedded systemMeasurement device
The invention provides a planar parallel mechanism end tracking control system based on a two-dimensional encoder and a planar parallel mechanism end tracking control method thereof. The system comprises a planar parallel mechanism, a two-dimensional encoder measurement device, a mechanism clearing device and a control device which are installed on a static platform. The control device is composed of a servo motor control module, a trigger photoelectric switch module, a parallel mechanism positioning control module and a parallel mechanism trace tracking control module. According to the whole system, firstly the end of the planar parallel mechanism is enabled to be located in the zero point through the mechanism clearing device, then the real-time position of the end of the planar parallel mechanism is measured through the two-dimensional encoder and then inputted to the control device, and the planar parallel mechanism is driven by the control device so that the end is enabled to be accurately positioned according to the preset traces. According to the control system and method, a data processing module involved can obtain the position of the end of the platform through simple resolving so that the real-time performance is great. Meanwhile, the end trace tracking precision of the planar parallel mechanism can also be enhanced so that the condition for realizing submicron level positioning precision is provided for the planar parallel mechanism.
Owner:SOUTH CHINA UNIV OF TECH

Stewart platform attitude measurement device and measurement method

The invention discloses a Stewart platform attitude measurement device. Axial directions of three coordinate axes of a movable platform coordinate system are respectively X, Y and Z, four tri-axial acceleration sensors are installed on the movable platform of the Stewart platform through four cushion blocks, two tri-axial acceleration sensors are symmetric to each other by using a coordinate origin Ob of the movable platform coordinate system and respectively arranged at two sides of the X axis, another two tri-axial acceleration sensors are symmetrically installed by using the X axis as the symmetric axis. The invention further discloses a measurement method adopted by the Stewart platform attitude measurement device, the acceleration component of the coordinate origin Ob of the movable platform with respect to the coordinate origin OI of a fixed platform and a movable platform rotation angle speed are obtained through a formula, so that the position and attitude parameters of the movable platform coordinate system with respect to the fixed platform coordinate system can be obtained. Through the adoption of the measurement device and measurement method disclosed by the invention, the centroid coordinate, the rotation angle and the rotation direction parameter of the Stewart platform can be directly obtained without complex computation.
Owner:GENERAL ENG RES INST CHINA ACAD OF ENG PHYSICS

Test piece rotation driving device for centrifugal overload test of solid rocket engine

PendingCN111855216AMeet the test requirements of lateral overload at different anglesBalance eccentric momentEngine testingRotational axisLoop control
The invention relates to the field of centrifugal experiments. The invention particularly discloses a test piece rotation driving device for a centrifugal overload test of a solid rocket engine. The device comprises a mounting bottom plate and a driving motor, the output end of the driving motor is connected with a ball screw nut pair, a first guide rail is arranged on the mounting bottom plate along the ball screw nut pair, a first sliding block is arranged on the first guide rail, a screw nut of the ball screw nut pair is connected with the first sliding block, and a moving seat is arrangedon the first sliding block. The device further comprises a rocker arm, a second guide rail is arranged on the rocker arm along the rocker arm, a rotating seat is slidably arranged on the second guiderail, and a rotating shaft is arranged on the rotating seat and rotationally connected with the moving seat. The driving device has the advantages that a speed reducer, the screw nut pair, the rockerarm and the like in the driving device are of labor-saving structures, and large torque can be provided; the driving device is controlled by a servo motor, driven by the ball screw nut pair and guidedby a guide rail sliding block pair, and full-closed-loop control is realized by an encoder, so that the whole system has very high control precision.
Owner:GENERAL ENG RES INST CHINA ACAD OF ENG PHYSICS

Intelligent computerized numerical control (CNC) spring machine

The invention discloses an intelligent CNC spring machine used for processing extension springs, compression springs, torsion springs, spiral springs and the like. The intelligent CNC spring machine comprises a straightening mechanism, a wire feeding mechanism, a pitch mechanism, a core seat mechanism, a knife seat mechanism and a computer control system. The pitch mechanism comprises a pitch servo motor and a pitch ball screw pair driving a pitch shaft to move; the core seat mechanism comprises a core seat lifting mechanism and a core rod core-pulling mechanism; and the knife seat mechanism comprises a plurality of sliding knife seats and knife seat driving mechanisms and can move along an arc-shaped track in a radial direction. The spring machine is provided with five sections includinga straightening section, a wire feeding section, a pitch section, a core seat section and a knife seat section according to the principle of spring formation, and has reasonable structure design and is driven by a full servo and controlled by a computer so as to realize fully closed loop control and be capable of reducing the rejection rate of finished products. The intelligent CNC spring machinecan be widely applied to the production of various extension springs, compression springs, torsion springs, spiral springs and the like, with simple operation, high processing precision and high production efficiency.
Owner:湖北伟斯科技有限公司

Control system for flexible tools for assembly of wing foreparts

The invention discloses a control system for flexible tools for assembly of wing foreparts. A single-axis servo motor on an SERCOS-III (serial real time communication specification-III) bus node is controlled through a motion controller, and therefore the motion control of a complete set of flexible tools for the assembly of the wing foreparts is realized, and the digital assembly of the wing foreparts is performed. The control system comprises a digital flexible tool, a laser tracker, a robot drilling system integration interface and a software integration platform, and all systems run harmoniously; control command and status return information interaction is implemented between the controller and an actuator unit; distributed motion control is performed on all shafts of the digital flexible tool; control is performed on the shafts of the flexible tool by an IPC (Industrial Personal Computer), and single-point location control is realized on each shaft; each shaft is provided with a grating ruler, and an actual position signal is measured, and is fed back to the control system to realize full-closed loop control of all the shafts. By changing the digital assembly process for the wing foreparts, servo control of different actions can be performed to realize the assembly of the wing foreparts of different types.
Owner:NORTHWESTERN POLYTECHNICAL UNIV +1

Vertical high-speed high-accuracy direct-driving mechanism

The invention relates to a vertical high-speed high-accuracy direct-driving mechanism. The mechanism comprises a vertically-placed base, vertically-placed sliding rails on the base, a primary linear motor and a secondary linear motor. The primary linear motor is installed on the base. The secondary linear motor is connected to a movable carrying plate, on which a sliding block is arranged. The sliding block is clamped on the sliding rails and move along the sliding rails. The primary linear motor and the secondary linear motor are arranged oppositely. The movable carrying plate is provided with a reading head. The base is further provided with a grating ruler used for sensing changes of the position of the reading head. The vertical high-speed high-accuracy direct-driving mechanism has following beneficial effects: by adoption of direct-driving technology of linear motors, extremely high acceleration and deceleration speed and motion speed are achieved; mechanical abrasion and opposite clearance are avoided; non-contact driving technology is utilized so that long service lifetime is realized; the base is made by large damping material so that value of amplitude for harmonic response of a lower-order mode is inhibited and vibration of the high-order mode is overcome; good dynamic response attribute is obtained; and by adoption of high-resolution position feedback device, full closed-loop control is achieved and the repeated accuracy is higher.
Owner:BOZHON PRECISION IND TECH CO LTD

Side-mounted precision angular displacement self-detecting system

The invention provides a system enabling a moving metal toothed body with circumferentially and mechanically halving characteristics to automatically perform precision angular displacement detection and output displacement information. The side-mounted precision angular displacement self-detection system designs a group of detection heads which comprise exciting, induction and compensation coils, arranged beside a moving metal body to be detected and work with a microprocessor system to accurately obtain motion displacement information of the moving metal body in a non-contact mode. The system is characterized in that the detection heads are additionally provided with axially-halved grooves, and a single coil is axially wound and tangentially connected in series to weaken magnetic field edge effects of the coil; tooth crests of metal winding bases of the detection heads are tangentially and axially machined into a particular arc respectively; the metal body to be detected and toothed portions of the detection heads comply with set distribution principles; the detection heads are provided with signal compensation coils with independently adjustable compensation power supplies; the metal body to be detected and the detection heads are regarded as an overall mechanical system with a sensing function, and an online or system error correction technology is used, so that the whole system can have the capability of self-detection and precision displacement information output.
Owner:重庆大族时栅科技有限公司

Crucible lifting and rotating mechanism special for silicon carbide furnace

The invention relates to the field of semiconductor equipment, in particular to a crucible lifting and rotating mechanism special for a silicon carbide furnace. The mechanism comprises a lifting mechanism, a rotating mechanism is installed on a lifting sliding table of the lifting mechanism, the rotating mechanism comprises a rotating shaft, and the rotating shaft is rotationally connected with the lifting sliding table through a magnetofluid rotary sealing piece; the periphery of the magnetofluid rotary sealing piece is connected with the lower end of a corrugated pipe device; the upper end of the corrugated pipe device is a corrugated pipe upper flange for connecting a silicon carbide furnace bottom cavity; the lower end of the rotating shaft is rotationally connected with a rotating joint which is provided with a water inlet and a water outlet; and a cooling loop is arranged in the rotating shaft, one end of the cooling loop is communicated with the water inlet, and the other end of the cooling loop is communicated with the water outlet. The magnetofluid rotary sealing piece is additionally arranged, so that the rotating effect and the high-vacuum sealing effect are achieved. High sealing performance between the rotating position and a silicon carbide furnace inner cavity is conveniently achieved, then the high vacuum degree of the silicon carbide furnace inner cavity can be guaranteed, and the mechanism is suitable for processing and production of third-generation semiconductor materials.
Owner:SHANGHAI HANHONG PRECISION MACHINERY

Synergetic control method of aircraft part pose alignment based on four locater

The invention discloses a method for adjusting and synergetically controlling the position and pose of an aircraft component based on four locators. The method comprises the following steps: firstly, a global coordinate system OXYZ is established, and the current position and pose and the target position and pose of the aircraft component are calculated under the global coordinate system; secondly, the automatic adjusting path and the inch adjusting path of the aircraft component are formed; thirdly, the track of the sphere pivot wiring point between the locator and the aircraft component is planed according to the automatic adjusting path and the inch adjusting path; fourthly, the track of the sphere pivot wiring point is inverted into the driving parameter of a 12 motor axle synchronouscontrol network; fifthly, the 12 motor axle synchronous control network is built based on a SynqNet bus, and the position servo of single motor axle adopts the full-closed loop digit controlling; andsixthly, two locators are selected, and the collocated relation between the locators is the master-slave motion mode. The method has the following advantages: firstly, the path for adjusting the position and pose of the aircraft component can be planed; secondly, the full-closed loop controlling of the single axle motion of the locator can be realized; and thirdly, the 12 axle synchronous motion of the position and pose adjusting system can be realized.
Owner:ZHEJIANG UNIV +1
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