77results about "Rotary gyroscopes" patented technology

The invention provides a photoelectric sensing inertial sensor and a manufacturing method thereof, and the sensor comprises a semiconductor substrate which is internally provided with an annular cavity; a light conduction device is arranged in a circle defined by the annular cavity and is used for transmitting light to the inner side wall of the circumference of the annular cavity along the radius; the light source is used for emitting light rays vertically emitted to the circumferential plane of the annular cavity; a modulation device is arranged in a vertical projection area of the light source to the plane where the light conduction device is located and used for modulating a light source beam to the radius direction of the annular cavity; the light receiving devices are uniformly arranged on the circumferential side wall of the outer side of the annular cavity; and the inertial body is located in the annular cavity and can rotate around the annular cavity, and when the inertial body rotates to the position of a certain light receiving device, the inertial body can shield the light receiving device to receive light beams. According to the invention, the miniaturization of the sensing device is realized, the manufacturing cost is greatly reduced, the comprehensive damping is small, the test error is low, and the impact resistance is higher.

The utility model relates to a low-stress high-stability gyroscope floater assembly which comprises a motor, a frame, two fastening lock nuts, two anti-loosening disc springs and a buoy, mounting holes are symmetrically formed in the two faces, perpendicular to the frame shaft, of the frame. Positioning tables are arranged at the outer ends of the mounting holes in the two sides, and buoy mounting tables are coaxially arranged at the two ends of the exterior of the frame; the fastening nuts at the two ends are fixedly connected with motor shafts at the two ends of the motor respectively, and the fastening nuts at the two ends are mounted in mounting holes in the two ends of the frame in an axial and radial limiting manner; anti-loosening disc springs are mounted between the positioning tables on the two sides of the frame and the fastening lock nuts in a pressing manner; the buoy sleeves are arranged on the buoy mounting tables at the two ends and are bonded and fixed with the buoy mounting tables; the motor shaft is made of a TiB2 / Al composite material; the frame, the fastening lock nut and the float bowl are made of 45% SiC / Al composite materials. The floater assembly is good in structural stability and beneficial to improving the precision of the gyroscope.

Provided is a two-degree-of-freedom ring frame repeated locking and circuit automatic switching gyro locking mechanism, which belongs to the technical field of inertial devices and comprises a shell, a shell cover arranged on the shell, an inner ring and an outer ring arranged in the shell, a limiting cam arranged on the inner ring, a locking pin elastically supported on the outer ring, and a locking cam arranged outside the outer ring; an electromagnet assembly is fixed on the shell cover, a torsional spring arm is installed in a U-shaped groove of the electromagnet assembly, an axle is positioned and installed through the torsional spring and a support arm hole to make the support arm generate a fixed shaft torque, an armature is installed in a hole of the electromagnet assembly, the armature is connected with the support arm through a pull rod, a pulley assembly and a limiting groove shaft are respectively riveted on a support arm bending space face positioning hole and are respectively used for precisely positioning the locking cam and the locking pin on the outer ring; the shell cover is symmetrically provided with two sides of an axis, and a normally open contact and a normally closed contact are respectively installed at an angle of 60° between the two sides. The gyro locking mechanism can realize the functions of gyro repeated locking reset, automatic switching and output of electric signals, and meets the requirements of automatic driving of a missile body.

A method of creating a privacy mask from an image imaged by an imaging device in which a rotation axis of a camera and a center of a lens do not match includes measuring a distance from the camera to an object in a first imaging condition; creating a first mask for the object, and storing the distance together with the first mask; and creating a second mask for the object in a second imaging condition and correcting a position of the second mask using the first mask and the distance, wherein an imaging angle of the camera in the first imaging condition is same as the imaging angle of the camera in the second imaging condition, and wherein a position of the lens in the first imaging condition is reversed around the rotation axis from a position of the lens in the second imaging condition.

The utility model discloses a gyroscope convenient to overhaul, which belongs to the technical field of gyroscopes, and comprises a mounting seat and a rotating arm arranged on the mounting seat, the rotating arm is provided with an upper support plate and a lower bearing plate which are fixedly connected with each other, a gyroscope main body is placed on the upper support plate, and the lower bearing plate is arranged on the lower bearing plate. A plurality of positioning bosses are arranged at the bottom of the gyroscope main body, and a positioning mechanism for locking the positioning bosses is arranged on the lower bearing plate; a cylindrical base is arranged on one side of the gyroscope body, and a first fixing ring is fixed to one end of the upper supporting plate and one end of the lower bearing plate. The positioning boss is locked through the positioning mechanism, so that the gyroscope body is stably installed, meanwhile, the gyroscope body is convenient to disassemble, and through cooperation of the first fixing ring and the second fixing ring, the gyroscope body can be conveniently disassembled. The upper supporting plate and the lower bearing plate can be conveniently detached from the cylindrical base station while the upper supporting plate and the lower bearing plate are stably mounted on the cylindrical base station, so that the overall disassembly and assembly are convenient, and the fault of the gyroscope main body can be conveniently overhauled.

The invention provides a rotation turn number counting method and device, computer equipment and a storage medium, and is applied to target equipment, the target equipment comprises a gyroscope, and the target equipment is in a rotation process; the method comprises the following steps: determining an angle difference between a next integer angle corresponding to a target integer angle and the target integer angle; the target integer angle is an integer angle corresponding to the first rotation angle, and the next integer angle corresponding to the target integer angle is an integer angle corresponding to the second rotation angle; the second rotation angle is a rotation angle acquired after the first rotation angle is acquired through the gyroscope; accumulating the angle difference to obtain an accumulated angle difference; and when the accumulated angle difference reaches the first preset angle, adding one to the number of rotation turns of the target equipment. According to the technical scheme, the number of rotation turns in the rotation process is counted, and the accuracy of the number of rotation turns is guaranteed.

The utility model discloses a kind of modular combination's magnetic type gyroscopes, it includes main module, two groups of transfer connecting part and sub module.Main module includes two back-to-back shaft connection's splicing block and rotatable center connecting block between it, center connecting block can rotate around shaft;Transfer connecting part inner end and splicing block outer end one-to-one clamping;Sub module each surface can be connected with center connecting block each rotating surface and transfer connecting part outer end surface magnetic attraction connection.Splicing block is connected by the first connecting shaft interference fit, center connecting block, the second component of transfer connecting part and sub module are all cubic structure, and corner is equipped with the round cavity with magnetic pearl, each surface four corners have the through-hole of intercommunicating round cavity.The utility model uses the way of magnetic attraction and clamping combination, realizes modular combination, connection is stable and dismounting flexible, can diversify splicing, improve interesting and creativity, solve the problem that traditional gyroscopes magnetic attraction end magnetic attraction is weak, structure stability is poor.

Hubless spin motor-based control moment gyroscope provides full three-axis attitude control for small satellites using compact control moment gyroscopes based on hubless spin Motors, arranged in a pyramidal configuration within the satellite. The present invention comprises an a hubless spin motor, a flywheel, a gimbal (nutation) motor, a slip ring, an encoder, and essential mechanical supporting components. The said flywheel is directly attached to the hubless spin motor's rotor, generating angular momentum in both clockwise and counterclockwise directions. The slip ring and encoder are integrated with the gimbal motor in the center of the hubless spin motor, facilitating power transfer and measuring the gimbal angle, respectively. The said Hubless spin motor-based Control Moment Gyroscope is integrated into limited spaces without sacrificing performance, achieved by optimizing the shapes and mounting positions of each component.

The invention discloses an operator position monitoring method, device and equipment and a medium, and the method comprises the steps: binding pre-obtained target operator information with corresponding business data, and generating a safety constraint of a target operator according to the business data; acquiring multi-source positioning data of the target operator in real time through a positioning terminal worn by the target operator, and inputting the multi-source positioning data into a preset neural network, so that the neural network performs data fusion on the multi-source positioning data to generate a correction position of the target operator; and through a preset reinforcement learning algorithm, according to the correction position and the security constraint, generating an optimal security path, and according to the optimal security path, carrying out monitoring and risk assessment on the current correction position of the target operator. According to the invention, the real-time performance and accuracy of the position monitoring of the operating personnel can be improved.

The present disclosure relates to an information processing apparatus, an information processing method, and a program capable of estimating an azimuth of a mobile object that is moving by an inertial measurement unit (IMU) alone with high accuracy. At least one of an acceleration and a velocity of a mobile object in a reference coordinate system is calculated on the basis of inertial navigation calculation, at least one of an acceleration and a velocity of the mobile object coordinate system that is a coordinate system of the mobile object is calculated from at least one of the acceleration and the velocity of the reference coordinate system, and a rotation component or an absolute azimuth is specified on the basis of at least one of the acceleration and the velocity of the mobile object coordinate system and reference information of at least one of an acceleration and a velocity serving as a non-holonomic constraint condition that constrains a degree of freedom of at least one of six axes related to an attitude and a velocity of the mobile object. The present disclosure can be applied to an inertial navigation system.

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 present invention relates to a gyro stabilizer assembly (1) for a marine vessel, comprising: a casing (2) defining a chamber (3) for supporting an at least partial vacuum; a flywheel (4) mounted within the chamber (3) for rotating about an axis of rotation (Z) under the partial vacuum; a flywheel shaft (5) on which the flywheel (4) is supported and mounted in the casing for rotation of the flywheel about the axis of rotation (Z), the flywheel shaft being rotatably supported by a first rotary bearing (6) at one end region of the shaft (5) and a second rotary bearing (7) at an opposite end region of the shaft (5); a lubrication system (8) configured to circulate lubricant (O) from a lubricant tank (9) to the rotary bearings (6, 7). The tank (9) is provided within or on the casing (2) to collect lubricant from the rotary bearings (6, 7) under the action of gravity, and the first and second rotary bearings (6, 7) are provided in the casing (2) for operation under the partial vacuum. The invention also relates to a vehicle, in particular a marine vessel, comprising the gyro stabilizer assembly (1).

This invention discloses a miniaturized micro-inertial north-finding instrument. The housing comprises three parts: a top cover, a base, and an aviation connector. A conductive slip ring is disposed at the lower part of the top cover and is connected to the rotation shaft of the rotor cover of the rotary drive structure through a circular hole, and is connected to the control circuit via wires. The rotary drive structure is disposed below the conductive slip ring and includes a rotor cover, an inertial device support, a rotor support, an inertial device, a coggingless motor, and an angular displacement sensor. The control circuit includes a data acquisition circuit and a motor drive circuit. The data acquisition circuit is connected to the inertial device to collect and transmit the output data of the inertial device, and the motor drive circuit is connected to the conductive slip ring to control and power the coggingless motor. This invention reduces the size of the north-finding instrument, making it more suitable for applications such as vehicle navigation, underground surveying, and weapon guidance. Furthermore, it allows for individual replacement, facilitating equipment inspection and maintenance.

A guidance method and system for calculating course correction when navigating includes using unintended radio frequency and / or unintended radiative emissions The guidance method and system for calculating course correction when navigating using unintended radio frequency and / or radiative emissions may generally include sensing the unintended radio frequency and / or unintended radiative emissions and then utilizing the sensed unintended radio frequency and / or the sensed unintended radiative emissions for navigation. The unintended radio frequency and / or the unintended radiative emissions sensed and utilized for guidance includes non-standard, ambient, third-party, or other radio frequencies or radiative emissions not originally designed for navigational purposes. Wherein, the utilizing the sensed unintended radio frequency and / or the sensed unintended radiative emissions includes calculating course corrections via the sensed unintended radio frequency and / or the unintended radiative emissions.

The invention relates to a special tool for testing and trimming mass distribution defects of an uncoated harmonic oscillator, and belongs to the field of testing and trimming of quartz hemispherical harmonic oscillators. The lower base and the upper base are each of a cylindrical structure which is vertically arranged in the axial direction. The upper base is coaxially arranged at the top of the lower base; the transmission shaft is axially and vertically arranged at the axis of the upper base and the lower base; the two groups of ball bearings sleeve the upper and lower ends of the transmission shaft respectively; the ball bearing located on the upper portion is arranged on the inner wall of the upper base. The ball bearing located on the lower portion is arranged on the inner wall of the lower base. Taper holes are formed in the top ends of the transmission shafts; the collet chuck is embedded into the taper hole; the locking nut is sleeved on the outer wall of the joint of the collet and the transmission shaft; the interdigital capacitor seat is coaxially arranged at the top end of the upper base; the interdigital capacitor is coaxially mounted at the top of the interdigital capacitor seat; the fixed stud is mounted at the top of the collet chuck; according to the invention, the uncoated harmonic oscillator and the interdigital capacitor can be fixed, the harmonic oscillator can rotate relative to the interdigital capacitor, and the gap between the harmonic oscillator and the interdigital capacitor is ensured.

A power tool including an implement driven by a motor; an inertial measurement unit; and a control circuitry in communication with the motor and IMU, wherein the control circuitry: receives motor data associated with a condition of the motor; determines angular change of the power tool from motion data received from the IMU or receives angular change data from the IMU; initiates a countdown timer in response to the condition of the motor reaching a threshold; and generates a control instruction to maintain power to the motor upon the countdown timer reaching a prescribed value if the angular change is greater than an angular change threshold at any time during a duration of the countdown timer and reduce power to the motor upon the countdown timer reaching the prescribed value if the angular change is less than the angular change threshold during an entire duration of the countdown timer.

Centrifugal gyroscopic devices are described herein. A representative device can include a shaft, an arm coupled to the shaft, a rotor coupled to the arm, and a control system operably coupled to the shaft, the arm, and / or the rotor. The shaft is rotatable about a first axis and the arm is configured to rotate with the shaft. The arm is pivotable about a second axis and the rotor is configured to pivot with the arm about the second axis. The rotor is further pivotable about a third axis. The control system is configured to bring the shaft, the arm, and the rotor into a resonant mode in which the shaft rotates at a rotational rate, the arm oscillates about the second axis at a first frequency substantially equal to the rotational rate, and the rotor oscillates about the third axis at a second frequency substantially equal to the first frequency.

A method for performing gyroscopic azimuth angle measurements includes estimating a pitch angle and a roll angle of a gyroscopic inclinometer in a wellbore; determining a measurement duration for each of the plurality of gyroscope measurements from the estimated pitch and roll angles; making each of the plurality of gyroscopic measurements at the determined measurement duration when the gyroscopes are disposed at a corresponding plurality of rotational positions in the tool housing; and calculating an azimuth angle of the wellbore from the plurality of gyroscopic measurements.

A gyroscope bearing system for a marine gyroscope has a bearing unit having an inner ring and an outer ring and a plurality of rolling members arranged between them. The bearing unit is configured to surround and support a part of a flywheel. Ais sleeve arranged around the outer ring. A locking plate is arranged on an inner side of the gyroscope relative to the bearing unit and the sleeve. The locking plate is movable between a first position where a vertical distance is present between the sleeve, the inner ring and a top face of the locking plate, and a second position where the locking plate is abutting the sleeve and the inner ring.

An orientation measurement device (1) is provided with: a first angular velocity sensor (11) that has a first detection axis (11D) extending in the horizontal direction and detects a first angular velocity about the first detection axis (11D); a rotation mechanism (13) having a rotation shaft (13R) extending in the vertical direction and rotating the first detection shaft (11D) of the first angular velocity sensor (11) about the rotation shaft (13R); and a second angular velocity sensor (12) for correcting the rotation angle (alpha) of a first detection axis (11D) in the rotation mechanism (13), the second angular velocity sensor (12) having a second detection axis (12D) extending in the vertical direction and detecting a second angular velocity with the second detection axis (12D) as the rotation center.

One of two earbuds according to one embodiment of the present disclosure comprises: a first wearing portion including a first microphone; a second wearing portion including a second microphone; a bridge physically and electrically connecting the first wearing portion and the second wearing portion and being formed to be bendable; a sensor including a Hall sensor configured to detect a change in magnetic force according to a positional relationship between the first and second microphones; a processor; and a memory connected to the processor, wherein the memory may be configured to store instructions that, when executed, instruct the processor to acquire first data indicating a wearing angle of the earbud from the Hall sensor, acquire second data indicating a magnetic force between the first and second microphones from the Hall sensor, and determine an effective distance between the first and second microphones with respect to an utterance point on the basis of the first and second data.

A robot may include a torque generator to generate a torque, and a leg system including one or more legs movably coupled to and supporting the torque generator. Each leg of the one or more legs may include a first leg member, a second leg member, a first joint movably coupling the first leg member and the second leg member, and a first linear elasticity element coupled between the first leg member and the second leg member across the first joint. The first linear elasticity element may be disposed to provide a first force when the first linear elasticity element is actuated that, in combination with the torque, facilitates maintaining an upright position of the bipedal robot.

A sensor assembly for a conveyor belt includes a load cell attachable to a link of a modular conveyor belt and configured to measure tension in the belt and a housing. The housing may include a first cavity configured to receive at least a portion of the load cell, and a second cavity configured to receive one or more electronic components.

The present invention relates to a MEMS gyrocompass, a method performed by the MEMS gyrocompass and a computer program product. The MEMS gyrocompass mitigates systematic error in determination of a north angle. The MEMS gyrocompass comprises at least one MEMS gyroscope having a sense axis within a reference plane. Samples from an output of the at least one MEMS gyroscope are obtained in at least two angles of rotation about an axis perpendicular to the reference plane. First fit coefficients are determined by fitting samples obtained from each individual MEMS gyroscope with first fitting functions determined as function of time. Second fit coefficients are determined by fitting components of earth rotation rate projected on the reference plane based on samples obtained by all of the at least one MEMS gyroscope, which fitting is performed with a second fitting function determined as a function of rotation angle of the at least one MEMS gyroscope with respect to a reference angle. The north angle is determined as an angle between the reference angle and true north based on the second fit coefficients.

An azimuth measurement device (1) includes a first angular velocity sensor (11), a rotation mechanism (13), and a second angular velocity sensor (12). The first angular velocity sensor (11) has a first detection axis (11D) extending in a horizontal direction and is configured to detect a first angular velocity around the first detection axis (11D) serving as a rotation center. The rotation mechanism (13) has a rotation axis (13R) extending in a vertical direction and is configured to rotate the first detection axis (11D) of the first angular velocity sensor (11) around the rotation axis (13R) serving as a rotation center. The second angular velocity sensor (12) is used to correct a rotation angle (α) of the first detection axis (11D) in the rotation mechanism (13). The second angular velocity sensor (12) has a second detection axis (12D) extending in the vertical direction and is configured to detect a second angular velocity around the second detection axis (12D) serving as a rotation center.

A centripetal gyro device is described in this specification. A representative device can include a shaft, an arm coupled to the shaft, a rotor coupled to the arm, and a control system operably coupled to the shaft, the arm, and / or the rotor. The shaft is rotatable about a first axis, and the arm is configured to rotate with the shaft. The arm is pivotable about a second axis, and the rotor is configured to pivotally rotate about the second axis with the arm. The rotor is further pivotable about a third axis. The control system is configured to bring the shaft, the arm, and the rotor into a resonant operating mode in which the shaft rotates at a certain rotational speed, the arm vibrates about the second axis at a first frequency substantially equal to the rotational speed, and the rotor vibrates about the third axis at a second frequency substantially equal to the first frequency.

A power tool including an implement driven by a motor; an inertial measurement unit; and a control circuitry in communication with the motor and IMU, wherein the control circuitry: receives motor data associated with a condition of the motor; determines angular change of the power tool from motion data received from the IMU or receives angular change data from the IMU; initiates a countdown timer in response to the condition of the motor reaching a threshold; and generates a control instruction to maintain power to the motor upon the countdown timer reaching a prescribed value if the angular change is greater than an angular change threshold at any time during a duration of the countdown timer and reduce power to the motor upon the countdown timer reaching the prescribed value if the angular change is less than the angular change threshold during an entire duration of the countdown timer.

A method for controlling a wearable device, according to one embodiment, may comprise the operations of: determining, on the basis of first sensor information received from the wearable device, a first type of terrain on which a user is walking; when it is determined that a preset first event associated with walking has occurred, determining a second type of terrain on the basis of a first type set including the first type; when it is determined that a preset second event associated with walking has occurred, determining a third type of terrain on the basis of a second type set including the second type; determining a target operation mode of the wearable device on the basis of the third type; and controlling the wearable device on the basis of the target operation mode.

The invention provides a variable capacitance gyroscope and a manufacturing method thereof, the variable capacitance gyroscope comprises a semiconductor substrate and an inertia body, an annular cavity is arranged in the semiconductor substrate, and a plurality of separated first capacitance plates which are uniformly arrayed along the circumference are arranged in the semiconductor substrate below the annular cavity; second capacitor plates which are uniformly arrayed along the circumference are arranged in the semiconductor substrate above the annular cavity, the first capacitor plates and the second capacitor plates are oppositely arranged in a one-to-one parallel manner, and the inertia body is positioned in the annular cavity and can rotate around the central axis of the annular cavity in the annular cavity. According to the invention, the miniaturization of the sensing device is realized, the manufacturing cost is greatly reduced, and the anti-impact capability is higher.

The utility model belongs to the technical field of north seeker, concretely is a kind of high-precision portable north seeker, it includes: north seeker main body, heat conduction fin and cooling mechanism, north seeker main body includes shell and heat conduction groove, the shell side wall is evenly distributed and is equipped with heat conduction groove;Heat conduction fin is connected on the heat conduction groove;Cooling mechanism is connected in the outer end of heat conduction fin, export the heat in the inside of north seeker by heat conduction fin, cooling mechanism is cooled to heat conduction fin, including cooling effect, cooling mechanism is arranged in the outside of north seeker, avoid the vibration generated when cooling mechanism works to influence normal work of north seeker.