2535 results about "Inertia force" patented technology

A robotic control system is placed in clutch mode so that a slave manipulator holding a surgical instrument is temporarily disengaged from control by a master manipulator in order to allow manual positioning of the surgical instrument at a surgical site within a patient. Control systems implemented in a processor compensate for internally generated frictional and inertial resistance experienced during the positioning, thereby making movement more comfortable to the mover, and stabler from a control standpoint. Each control system drives a joint motor in the slave manipulator with a saturated torque command signal which has been generated to compensate for non-linear viscous forces, coulomb friction, cogging effects, and inertia forces subjected to the joint, using estimated joint angular velocities, accelerations and externally applied torques generated by an observer in the control system from sampled displacement measurements received from a sensor associated with the joint.

Disclosed herein are muscle-back iron golf clubs that have improved mass qualities to provide higher rotational moments of inertia and lower center of gravity while retaining the workability of muscle-back irons and the size, shape and dimensions preferred by tour players and low handicap players.

Method and apparatus for increasing the transmissibility of inertial forces produced by an inertial actuator on the housing of a tactile feedback interface device. A tactile interface device, coupled to a host computer, outputs tactile sensations to a user based on interactions and events occurring in a displayed graphical environment. An actuator produces periodic inertial forces, such as vibrations, and a compliant suspension couples the actuator to the device housing. A compliance of the suspension is selected such that the suspension magnifies the periodic inertial forces for a particular frequency range of the inertial forces. The magnified inertial forces are transmitted to the housing to be felt by the user.

The invention relates to a magnetic fluid damping device, which is suitable for damping long objects in spacecrafts and solves the problem of the damping of the long objects in the spacecrafts. The device comprises a non-magnetic shell (2), magnetic liquid (3), a permanent magnet (4), a nut (5), an end cover (6), a bolt (7), a screw (9), a sealing gasket (10) and an O-shaped seal ring (11). The parts are connected in a way that: the permanent magnet (4) is arranged in the non-magnetic shell (2); the end cover (6) with the O-shaped seal ring (11) is fixed to one end of the non-magnetic shell (2) by the bolt (7) and the nut (5); the magnetic liquid (3) is filled into the non-magnetic shell (2) by a threaded hole (8); and the non-magnetic shell (2) is sealed by the screw (9) and the sealing gasket (10). The device is sensitive to inertia force, can perform damping on the vibration with the characteristics of low frequency, small displacement and low accelerated speed, and has long service life and simple assembly method.

Provided is a vehicle testing apparatus which involves load variation and alignment variation, for analyzing a maneuverability of a vehicle on flat belts or rollers adapted to be rotated together with wheels of the vehicle, and in particular, maneuver variation. Load variation caused by an inertia force and a gravitational force which are produced during actual running of the vehicle, and tire alignment variation caused by suspension strokes, are forcibly reproduced by forces produced by actuators or a gravitational force, thereby it is possible to evaluate a maneuverability of the vehicle in a condition substantially the same as that during actual running of the vehicle.

A robot having joints includes a position information acquiring section that acquires time series information about a robot position, speed information, or acceleration information, a dynamics parameter switching section that switches a gravity term component and an inertia force term component of a motion equation separately between dynamics parameters including dynamics parameter of the robot gripping no object and dynamics parameter including the object gripped by the robot which robot arm gripping the object, and a desired torque calculation section that outputs a desired robot joint torque value as a desired joint torque based on the motion equation after the dynamics parameter switching section switches the dynamics parameters and the time series information about the robot position, the speed information, or the acceleration information acquired by the position information acquiring section. The robot controls an operation of the robot based on an output from the desired torque calculation section.

The invention discloses a magnetic liquid damping shock absorber with an arc-shaped inner wall axial section, which is suitable for shock absorption for a long object in a spacecraft. The device comprises a non-magnetic-conducting shell (1), a bolt (2), a nut (3), a permanent magnet (4), a magnetic liquid (5), a non-magnetic housing (6), an O-shaped ring (7), air hole (8), a shell inner wall surface (9) with an arc-shaped inner wall axial section, an air hole (10) and an interlayer air gap (11), wherein connection among the various portions above is as follows: the permanent magnet (4) is installed in the non-magnetic-conducting shell (1), the magnetic liquid is coated on the permanent magnet (4), and the non-magnetic housing (6) and the non-magnetic-conducting shell (1) are sealed by the O-shaped ring (7), and rigidly connected by the bolt (2) and the nut (3); the inner wall axial section of the non-magnetic-conducting shell (1) is arc-shaped, and the corresponding central angle theta is 1-15 degrees. The device is quite sensitive to an inertia force, and capable of carrying out effective shock absorption on shock with the characteristics of a low frequency, a small displacement and a low accelerated speed.

A headrest control apparatus includes: a headrest moving mechanism that supports a headrest in such a manner that at least one of a rotation of the headrest about an axis of the headrest, which extends in the vehicle-height direction, and a movement of the headrest in the vehicle-width direction is permitted; a drive unit that causes at least one of the rotation and the movement of the headrest; and a control unit that controls the drive unit.

A detector device includes a drive circuit for outputting a drive pulse signal for displacing the variable block, a detection pulse signal applying unit by which the variable capacitance elements and the fixed capacitance element whose one end is connected in common are respectively applied, at their other ends, with detection pulse signals with a plurality of phases each having a predetermined phase difference at a timing synchronized with the drive pulse signal, and an inertia detection unit for detecting a difference in capacitance value between the variable capacitance elements to which the detection pulse signal having the phase difference is applied, or between the fixed capacitance element and the variable capacitance element, and detecting the applied inertial force based on the difference.

In a hinge structure suitable for use in a foldable mobile phone, the initial unfolding action is effected by converting a pushing stroke of an operating member into a rotational movement of the hinge by using a cam / cam follower mechanism. Thereby, an unexpected reaction force resulting from the inertia force acting between the two parts that are to be unfolded relative to each other can be avoided, and a favorable unfolding action without a shock can be achieved. In particular, it may be arranged such that the hinge is normally urged in the unfolding direction while a clutch is kept engaged to retain the hinge in the fully folded state, and that the hinge is resiliently driven in the unfolding direction by pushing the operating member and thereby disengaging the clutch.

The invention discloses a friction and abrasion testing method and equipment of cylinder piston ring element in the friction and abrasion testing technique domain, which is characterized by the following: adapting mechanic radial loading construction method and equipment to test the cylinder and piston ring element; adding liquid through heating the cylinder cavity to keep thermal; fixing the friction force sensor on the test machine rack directly; eliminating the measuring result influence of friction force by inertia force of moving component to gain more precise friction force; segregating the friction force sensor and cylinder through thermal-insulation material; setting the cooler to prevent the rack temperature from elevating and the temperature of friction force sensor from exceeding the highest working temperature. The invention is used as the rapid assessment method in the lab developing procedure of cylinder piston ring.

The present haptic feedback interface device uses electroactive polymer (EAP) actuators to provide haptic sensations and / or sensory capabilities. The tactile feedback interface device is in communication with the host computer (14) and includes a sensor (112) device for detecting user manipulation of the interface device and an electrical device for outputting to the user the force generated by the movement of the actuator in response to the input signal. Active polymer actuator (18). The output force provides a tactile sensation to the user. Various embodiments of interface devices using EAP actuators are described, including embodiments providing direct force, inertial force, and braking force.

A method for presenting an analyte of a liquid sample as an MS-analyte to a mass spectrometer. The method is characterized in (a) comprising the steps of: (i) applying the liquid sample to a sample inlet port (I) of a microchannel structure (I) of a microfluidic device, said structure also comprising an MS-port, (ii) transporting the analyte by a liquid flow in microchannel structure (I) thereby transforming the analyte to an MS-analyte, and (iii) presenting the MS-analyte to a mass spectrometer via the MS-port, and (b) using inertia force for creating said liquid flow within at least a part of microchannel structure (I). A microfluidic disc comprising (a) an axis of symmetry perpendicular to the plane of the disc, (b) a microchannel structure (I) comprising an inner application area at a shorter radial distance than an outlet port, and an MS-port and a sample inlet port (I).

Disclosed is a working machine that computes and displays moment by moment its dynamic stability and its state of contact with a ground in view of an inertia force and an external force applied to the working machine. Specifically, a working machine is provided with an undercarriage, a working machine main body mounted on the undercarriage, a front working mechanism attached pivotally in an up-and-down direction to the working machine main body, and a working attachment connected to a free end of the front working mechanism. The working machine includes a ZMP computing means for calculating coordinates of a ZMP by using position information, acceleration information and external force information on respective movable portions of the main body, which includes the front working mechanism, and undercarriage, and a stability computing means for calculating a support polygon formed by plural ground points of the working machine with a ground, and, when the ZMP is included in a warning region formed inside a perimeter of the support polygon, producing a tipping warning sound. The ZMP and the support polygon, which includes the warning region, is computed, and a display or warning is produced.

The invention relates to the technical field of shield machine speed reduction, and discloses a soil pressure balance shield machine cycloid speed reducer. The soil pressure balance shield machine cycloid speed reducer is characterized in that: a cycloid driving part is arranged in a cavity formed by connecting a front end cover with a back end cover by using a pin wheel housing, wherein a half-buried hole of the pin wheel housing is in movable fit with a sleeveless needle pin; four cycloidal wheels are arranged on a double-eccentric bearing, wherein the phase difference between a first cycloidal wheel and a second cycloidal wheel and between a third cycloidal wheel and a fourth cycloidal wheel is 180 degrees, and the second cycloidal wheel and the third cycloidal wheel have the same phase; and a W output mechanism consists of an output shaft, a pin and a uniform loading plate, the pin is provided with three circular ring plates to form a four-section freely supported structure, and the W output mechanism is supported in an inner hole of a front end cover and an inner flange outer circle of a back end cover through a bearing respectively. The soil pressure balance shield machine cycloid speed reducer has the following advantages that: (1) the axial size is 45 to 55 percent shorter than that of a third-class planetary reduction gear of the background art; (2) the cycloidal wheels can be assembled in a reversed mode to double the service life; (3) the manufacturing cost is 40 to 50 percent of that of the third-class planetary reduction gear of the background art; and (4) the inertia force and the inertia moment in operation are theoretically completely balanced.

The invention relates to a non-linear dynamic finite element method for determining cable-strut system static balancing state. In the construction processes of traction mounting and stretch-draw forming, a cable-strut system as a mechanism has super large displacement, mechanism displacement and guy cable looseness, and a conventional linear dynamic finite element method cannot obtain the static balancing state in the construction stage. The non-linear dynamic finite element method adopts form-finding analysis to establish a non-linear dynamic finite element equation by introducing inertia force and viscous damping force so as to change a static problem which is difficult to solve into a dynamic problem which is easy to solve, and gradually converge the dynamic balancing state of the cable-strut system into a static balancing state through iteration updating of the configuration of the cable-strut system. The cable-strut system is in a static unbalancing state before analysis, is in the dynamic balancing state in the analysis, and reaches the static balancing state after the convergence, namely the cable-strut system discontinuously moves (non-continuous movement) from the initial static unbalancing state to the stable static balancing state.

A vehicle headrest apparatus has a headrest unit mounted to an upper end of a seatback. The headrest unit has a headrest members with a head restraining member configured to be tensioned to restrain a passenger's head upon a rear-end collision. The headrest unit quickly and reliably restrains a seated passenger's head during a rear-end collision without utilizing the inertia force of the passenger's body by detecting the rear-end collision and pushing the headrest unit only outward in the forward direction of the vehicle. The headrest unit also has a swing / pushup device that to pushes the headrest members upwardly and forwardly. An auxiliary swing force adding device applies an auxiliary spring force in the deployment direction of the headrest members to increase the deployment speed of the headrest members and shorten the amount of time required to achieve initial contact between the passenger's head H and the head restraining member.

Gravity center position GRA of image display device 15 is, in a human state of standing, located in a more backward position compared with eyeball 9 and in a more downward position compared with eyeball 9. In this case, assuming that the rotation axes of the head are the X-axis, the Y-axis, and the Z-axis, the intersection point of these axes is the head's rotational movement center CNT. By this, GRA comes close to CNT, and thus, even when rotational movement of the head occurs around CNT, inertia forces other than moment of inertia are successfully made small. Therefore, the image display device can smoothly follow the movements of human head even if the device is heavy in weight.

The invention discloses a full-firing-direction autonomous reentry guidance method based on a three-dimensional reentry trajectory analytical solution. The full-firing-direction autonomous reentry guidance method comprises the following steps of 1, building of a kinematical equation and a dynamical equation, 2, summarizing of the reentry guidance method, 3, descent stage guidance strategies, 4, steady gliding stage guidance strategies and 5 height-adjustment stage guidance strategies. The full-firing-direction autonomous reentry guidance method has the advantages that reentry guidance of an aircraft with the large lift-drag ratio can be guided effectively, low-damping and long-period trajectory oscillation caused by the high lift-drag ratio can be restrained effectively, the peak value ofthe heat flux density is reduced, and tracking of a reference track is facilitated; inertia force caused by earth rotation and actual aerodynamic force are combined into equivalent aerodynamic force,an equivalent aerodynamic section is planned through the analytical solution, and thus the aircraft has the omni-directional reentry task processing capability; and an equivalent aerodynamic section fitting formula based on the inverse proportional function is put forward, the reentry trajectory analytical solution based on the complex equivalent aerodynamic section form is further deduced, and thus high precision, all-dimensional applicability and high robustness are achieved.

The invention provides a fiber bragg grating high-frequency acceleration sensor based on flexible hinges. The fiber bragg grating high-frequency acceleration sensor based on the flexible hinges is composed of a composite base body, an optical fiber and a sensor shell. The composite base body is fixedly arranged in the sensor shell and composed of a base, the two flexible hinges and two inertia mass blocks. The two inertia mass blocks are connected with the base through the flexible hinges respectively, the two sides of the connecting portion are provided with horizontal notches respectively, and a vertical notch is vertically formed between the two inertia mass blocks. The optical fiber penetrates through the two sides of the sensor shell and is arranged in symmetrical optical fiber grooves formed in the two inertia mass blocks. The optical fiber between the two optical fiber grooves is provided with a bragg grating. The bragg grating is arranged at a groove in the center of the position between the two inertia mass blocks. The optical fiber located in the optical fiber grooves is bonded and fixed to the inertia mass blocks through adhesives. The fiber bragg grating high-frequency acceleration sensor based on the flexible hinges is integrated in core structure and convenient to install; the two inertia mass blocks are in lateral symmetry, so that tension strain of the fiber bragg grating bearing inertia force is multiplied, and the sensitivity of the sensor is greatly improved.

The invention relates to a zero-force control method and system for a robot. The zero-force control method comprises the following steps: S1, a robot kinetic model is built on the basis of inertia force, centrifugal force, coriolis force, viscous friction force, static friction force and gravity; S2, external force moments of all the joints of the robot are calculated on the basis of the robot kinetic model and feedback data; S3, a speed command is calculated according to the external force moments calculated in the step 2; and S4, a position command is calculated according to the speed command and position feedback. Through the building of the kinetic model, the external force moments of all the joints can be directly calculated, without the assistance of a power-assisted sensor or a torque sensor, so that the cost and the complexity of the system are reduced; by the adoption of a position command control manner instead of a direct torque control manner, the design difficulty in the safety and the stability of the system is reduced; and in addition, since inertia force is considered when the external force moments are calculated, the zero-force control method and system can be suitable for robots with greater dead weight.

An inertial force sensor includes a weight, a first fixing portion linked to the weight, a second fixing portion linked to the weight via the first fixing portion, a first electrode on a first surface of the weight, a second electrode facing the first electrode, and first and second elastic portions elastically deforming so as to displace the weight. The first elastic portion displaces the weight along an X-axis but not along any of a Y-axis and a Z-axis. The second elastic portion displaces the first fixing portion along the Y-axis but not along any of the X-axis and the Z-axis. This inertial force sensor detects an acceleration at high sensitivity.

The invention discloses a magnetic liquid damping vibration attenuation device which is suitable for longer object vibration attenuation in a spacecraft and can be used for solving the vibration attenuation problem of longer object vibration attenuation in the spacecraft. The magnetic liquid damping vibration attenuation device comprises an end closure (1), a magnetic liquid (2), a non-magnetic-conductive shell (3) and a permanent magnet (4), wherein the permanent magnet (4) is installed in the cavity of the non-magnetic-conductive shell (3), the magnetic liquid (2) is injected into the cavity of the non-magnetic-conductive shell (3) and the end closure (1) is used for sealing. The device is very sensitive to the inertia force, the adopted end closure (1) with threads is provided with a taper angle, the taper angle is 140degrees -170degrees, the depth of the end closure screwed into the non-magnetic-conductive shell (3) can be adjusted so as to regulate the pressure applied to the magnetic liquid by the end closure (1), the permanent magnet is a cylinder, the vibration attenuation effect is good for the vibration with low frequency, small displacement and small acceleration characteristics.

A piezoelectric-driven 2-D stage (X-Y axis) utilizing the frictional stick-slip effect and inertia force can be designed and fabricated to achieve ultra high resolution and long travel range. Based upon the principle of elastic deformation, a high resolution piezoelectric-driven micropositioner (Z-axis) is designed and fabricated. Moreover, a CD pick-up head and analog linear controller are integrated with Z-axis micropositioner to be a autofocus system. This design is based upon the requirement of the optical lithography developments by using 193 nm Excimer Laser. During this special lighography process, Z-axis micropositioner is needed for the laser beam focusing. A 2-D X-Y stepper is also needed for the movement of the wafer under laser exposure. The wafer stepper is based on the step-repeat and step-scan process.

A directly coupled-inertia activated mechanism that may be incorporated into a door handle assembly and counteracts inadvertent door opening during a side crash. An inertia lever with certain inertia moment in relation ship to that of the handle is coupled to the handle, such that it rotates in the opposite direction of that of the handle when the handle is being pulled. The inertia lever is capable of canceling totally the inertia force causing the handle to move inadvertently to unlatched position during side impact crash, and stops the handle's unlatching move.

The invention discloses a reciprocal high-temperature high-load friction and abrasion test method and equipment in the friction and abrasion testing technique domain, which is characterized by the following: the reciprocal moving structure, lower sample bottom support structure and upper sample vertical location structure adapt standard rolling bearing to realize the dynamic part measurement of friction coefficient, which improves the accuracy greatly; the load is constructed precisely to exclude the interference of sample moving structure friction force by static friction; the standard bearing improves the bearing ability, whose maximum load of nominal construction reaches 10000N to reduce the quality of moving structure and reciprocal inertia force and make the system operate stably at 800r / min; because of the orientation heating and thermal action of sample, the sample gains higher temperature and the bottom temperature remains low; the rolling shaft supports the bottom of sample bearing floor to keep enough space for cooling and lubricating through lubrication oil.

The invention relates to an optical fiber acceleration sensor based on an ultrashort cavity optical fiber laser, which is characterized by comprising: an equal strength socle beam which is an isoceles triangle and can convert an end inertia force into an even strain on the surface; an inertial quality block which is fixed on one end of the equal strength socle beam to produce inertia forces; and an optional fiber laser which is fixed on the central axis line above the equal strength socle beam to convert the strain into the change of the lasing wavelength of the laser.

The invention provides an insect-scale flapping-wing micro aerial vehicle actuated by piezoelectricity. The insect-scale flapping-wing micro aerial vehicle comprises a piezoelectric actuator, an aerial vehicle body, a transmission mechanism, two wings, two driven twisting hinges and auxiliary structures, wherein the aerial vehicle body and the transmission mechanism are integrally formed; the piezoelectric actuator generates cyclical reciprocating vibration under the situation of electrifying; the transmission mechanism is used for amplifying the micro vibration of the piezoelectric actuator and converting the amplified vibration into the flapping motion of the two wings; and each of the root parts of the two wings is connected with the corresponding driven twisting hinge, under the effect of aerodynamic force and inertial force, the two wings are twisted, so that lifting force required by flying is generated. According to the insect-scale flapping-wing micro aerial vehicle actuated by piezoelectricity disclosed by the invention, the size and the weight of the micro aerial vehicle are in an insect scale; the transmission mechanism with amplified flexible hinges is designed between the piezoelectric actuator and the wings, and is matched with the piezoelectric actuator, so that high-frequency wide-range reciprocating flapping motion of the wings can be realized; and the transmission mechanism and the aerial vehicle body are integrally designed, so that assembly of the transmission mechanism and the aerial vehicle body is avoided, and the assembling accuracy is greatly improved.

A pipeline pig includes a venturi and a modulating valve located rearward of the inlet side of the venturi. When the valve is in the open position, a predetermined maximum bypass flow is allowed through the venturi. The closed position allows a predetermined minimum bypass flow. The valve may be a poppet-style valve or a frusto-conical shaped stopper. The stopper has sufficient mass and / or aerodynamic drag to overcome the spring force holding the valve in the open position. When the pig stalls, the valve closes and the stopper chokes bypass flow through the venturi. When the pig starts running again, the valve opens as inertia forces the stopper away from the inlet side of the venturi. Also, as friction of the pig increases due to changes in the internal diameter of the pipeline or accumulation of debris ahead of the pig, increased airflow across the valve creates drag sufficient to partially overcome the spring force, thus keeping the pig moving at a desirable rate of travel.