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875 results about "Servomechanism" patented technology

In control engineering a servomechanism, sometimes shortened to servo, is an automatic device that uses error-sensing negative feedback to correct the action of a mechanism. It usually includes a built-in encoder or other position feedback mechanism to ensure the output is achieving the desired effect.

System and method for remote endoscopic surgery

A teleoperator system with telepresence is shown which includes right and left hand controllers (72R and 72L) for control of right and left manipulators (24R and 24L) through use of a servomechanism that includes computer (42). Cameras (46R and 46L) view workspace (30) from different angles for production of stereoscopic signal outputs at lines (48R and 48L). In response to the camera outputs a 3-dimensional top-to-bottom inverted image (30I) is produced which, is reflected by mirror (66) toward the eyes of operator (18). A virtual image (30V) is produced adjacent control arms (76R and 76L) which is viewed by operator (18) looking in the direction of the control arms. By locating the workspace image (30V) adjacent the control arms (76R and 76L) the operator is provided with a sense that end effectors (40R and 40L) carried by manipulator arms (34R and 34L) and control arms (76R and 76L) are substantially integral. This sense of connection between the control arms (76R and 76L) and end effectors (40R and 40L) provide the operator with the sensation of directly controlling the end effectors by hand. By locating visual display (246) adjacent control arms (244R and 244L) image (240I) of the workspace is directly viewable by the operator (FIGS. 12 and 13). Use of the teleoperator system for surgical procedures is also disclosed (FIGS. 7-9 and 13).
Owner:SRI INTERNATIONAL

Novel multi-redundancy electromechanical hydrostatic servo mechanism

InactiveCN103075393AOvercoming the defect of easy cloggingAdapt to high reliability requirementsFluid-pressure actuator componentsControl vectorElectric machine
The invention belongs to a thrust vector control servo system for a manned space carrier rocket or missile which has a demand for high reliability to provide thrust for an engine or a steering engine on the rocket or the missile, and particularly relates to a novel multi-redundancy electromechanical hydrostatic servo mechanism. The novel multi-redundancy electromechanical hydrostatic servo mechanism has the advantages that since a servo motor is directly used for driving a bidirectional rotating constant plunger pump, the defect that a valve-controlled electro-hydraulic servo system is apt to be blocked is overcome and the requirement of high reliability is satisfied; since a controller, a motor driver, a servo electric pump and a displacement sensor adopt multi-redundancy configuration, under the situation of at most two-redundancy faults, the system can still work normally and the feasibility of high reliability is guaranteed from structural design; since peak power is provided for a load through the maximum overload of an alternating-current permanent magnet motor and the alternating-current permanent magnet motor is designed according to load average power, compared with an alternating-current permanent magnet motor which is designed according to load maximum power, the size is small, the weight is light and the requirements on long-term use, light weight and small size are better satisfied.
Owner:BEIJING RES INST OF PRECISE MECHATRONICS CONTROLS +1

Method for identification of rotational inertia of AC servo

The invention relates to a rotary inertia identification method of an alternating-current servomechanism, the load inertia and the rotor inertia of a motor are regarded as a whole inertia, a servo system does an accelerated motion and a decelerated motion, so as to obtain the system output torque and the motor average rotate speed for a period of time. The average torque of the servo system can be obtained by the system output torque, the value of the whole inertia can be obtained according to the motor average rotate speed, the average torque of the servo system, and the total operation time of the accelerated motion and the decelerated motion of the system, that is, the rotary inertia of the alternating-current servomechanism can be identified. The invention does not need to singly identify the load inertia or the load torque for identifying the system rotary inertia, but causes the load inertia and the motor rotary inertia to be regarded as an inertia, and the identification of the system rotary inertia can be realized by combining the system output torque. The implementation of the method is simple, the use is convenient, the identified inertia precision is higher, and the method can be applied to the servo system inertia detection of a permanent magnetism synchronous servo-actuator.
Owner:ESTUN AUTOMATION TECH

Carrier rocket sub-stage falling area range control system

ActiveCN110160407AReal-time monitoring of air positionQuick searchSelf-propelled projectilesCarrying capacityControl system
The invention discloses a carrier rocket sub-stage falling area range control system. The carrier rocket sub-stage falling area range control system comprises a grid fin structure system, a grid fin control system, a grid fin telemetering system and a ground information receiving system. Under the condition that a control unit resolves the measurement information such as the posture, the positionand the speed, a servo mechanism is controlled to deflect the fin surface by sending an instruction, so that the posture of a sub-stage of a carrier rocket is stabilized, and the sub-stage is guided to fly to the target falling area for flying landing; and the telemetering system and the ground information receiving system are used for measuring and receiving the sub-stage reentry flight information, and the sub-stage state information is monitored in real time. According to the system, the flight control time sequence and procedures are integrated, so that the sysrem has the advantages that the modification amount of the carrier rocket is small, the loss of the carrying capacity is small, the flight safety of a main task of the carrier rocket is not affected, the sub-stage falling area range of the carrier rocket can be greatly reduced, and the sub-stage return information can be monitored in real time.
Owner:SHANGHAI AEROSPACE SYST ENG INST

Electric servo mechanism load simulation system and simulation method thereof

The invention provides an electric servo mechanism load simulation system and a simulation method thereof. The system comprises a pedestal, a tested servo mechanism and a force moment loading mechanism which are disposed on the pedestal, a rigidness simulation mechanism, a friction simulation mechanism, an inertia simulation mechanism, a torque sensor, an angle sensor, and a central processing unit, wherein the rigidness simulation mechanism, the friction simulation mechanism, the inertia simulation mechanism and the torque sensor are disposed between the tested servo mechanism and the force moment loading mechanism, and the angle sensor is used for measuring the position and speed of the force moment loading mechanism. The rigidness simulation mechanism is connected with a rotor of the tested servo mechanism, and is driven by the rotation of the tested servo mechanism to swing. The friction simulation mechanism, the inertia simulation mechanism and the force moment loading mechanism are located in the same main axis, and are respectively used for simulating a friction load, an inertia load and an elastic load. The central processing unit receives detection signals of the torque sensor and the angle sensor, and judges whether the force moment parameter indexes of rotation inertia, rigidness, rotation speed and simulation position meet the requirements of performance testing under the condition of different loads or not.
Owner:BEIJING JIAOTONG UNIV

Active vision non-contact type servomechanism parameter measurement method and apparatus thereof

InactiveCN101424551AReduce difficultyAutomatically adjust shutter speedUsing optical meansMeasurement deviceAngular velocity
The invention provides an active vision non-contact servo mechanism parameter measuring device, consisting of a measuring screen, a servo mechanism mounting platform, an image acquiring and processing system, and a red light laser light source, wherein a servo mechanism to be detected is provided with the red light laser light source which is positioned on the servo mechanism mounting platform and is arranged in front of the measuring screen, a digital camera is arranged behind the measuring screen to image on the screen. Firstly, the device shoots a picture of a gridiron pattern on the measuring screen by the camera which is demarcated; secondly, the servo mechanism controls a main frame to give a command so as to control the rotation of the servo mechanism to be detected, a computer extracts laser point coordinates of the image, the rotational angle at each moment of the servo mechanism to be detected is calculated and recorded in real time, the motion parameters of the servo mechanism to be detected such as the angular velocity, the pointing accuracy, and the overshoot are calculated by the rotational angle; the measuring method is simple, convenient and flexible, and the device and the measuring method realize the measurement in real time and with high accuracy of the movement parameters of a biaxial servo mechanism through the non-contact way.
Owner:BEIHANG UNIV

Autopilot flight control system

The invention relates to an autopilot flight control system. The autopilot flight control system comprises a flight control panel, a radio station, a servo mechanism, a receiver and a remote controller, wherein the radio station is communicated with the flight control panel in a two-way mode on remote control and telemetering, the servo mechanism receives servo control instructions of the flight control panel, the receiver transmits manual control instructions to the flight control panel, and the remote controller transmits remote manual control instructions to the receiver. The flight control panel further comprises a central processing module, a communication module which communicates with the central processing module in a two-way mode, a sensor module which communicates with the central processing module in the two-way mode, and a servo output module which receives instructions of the central processing module, wherein the communication module of the flight control panel receives instructions of the receiver and communicates with the radio station in the two-way mode. The radio station communicates in the two-way mode with a ground control system outside the autopilot flight control system. The servo output module transmits servo information to the servo mechanism. The autopilot flight control system is small in structure, simple and clear in system design, high in computation efficiency and reliability and very good in expansibility and portability.
Owner:天津全华时代航天科技发展有限公司
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