Gyroscope Control Patents (Class 74/5.4)
  • Patent number: 9683843
    Abstract: A vibrator element has a first vibration mode in which first and second detection portions perform flexural vibration in opposite directions in the opposite phase to first and second driving portions which vibrate in opposite directions according to a Coriolis force, and a second vibration mode in which the first and second detection portions perform flexural vibration in opposite directions in the same phase as the first and second driving portions which vibrate in opposite directions according to a Coriolis force. A ratio r=R2/R1 of equivalent series resistance R2 at the time of the second vibration mode to equivalent series resistance R1 at the time of the first vibration mode is set between 0.15 and 6.0.
    Type: Grant
    Filed: March 26, 2014
    Date of Patent: June 20, 2017
    Assignee: Seiko Epson Corporation
    Inventors: Keiji Nakagawa, Ryuta Nishizawa
  • Patent number: 9471539
    Abstract: Methods and devices for determining a noise variance of an axis of a gyroscope are described. In one aspect, the method includes: representing a plurality of gyroscope readings for the axis in a histogram, the histogram including a plurality of bins associated with respective ranges; determining a bias for the axis of the gyroscope by identifying a concentration of the gyroscope readings within the histogram; and determining a noise variance for the axis of the gyroscope based on the histogram and based on the identified concentration of gyroscope readings.
    Type: Grant
    Filed: August 24, 2012
    Date of Patent: October 18, 2016
    Assignee: BlackBerry Limited
    Inventors: Nathan Daniel Pozniak Buchanan, Robert Oliver, Adam Louis Parco
  • Patent number: 9419597
    Abstract: Embodiments of the present invention eliminate the high bandwidth buffer from the analog chopper circuit. In some specific embodiments, the buffer is replace with a comparator-based loop that can be used to apply offset correction and achieve N-bit settling performance with sharp (up to 1 ns) rise and fall time with significantly lower power than with a buffer. Other specific embodiments include overcharging circuitry in combination with the comparator-based loop or in lieu of the comparator-based loop. Still other specific embodiments include an array of capacitors in place of the single large capacitor Clarge and use decoding/switching circuitry to selectively couple one of the capacitors into the circuit based on the DAC input code. Importantly, exemplary embodiments result in total power dissipation around the theoretical limit needed to charge the capacitor to the DAC output voltage.
    Type: Grant
    Filed: June 15, 2015
    Date of Patent: August 16, 2016
    Assignee: Analog Devices Global
    Inventors: Achal Venkatesh, Abhinav Kumar Dikshit
  • Publication number: 20150143932
    Abstract: Gyroscopic systems to stabilize vehicles and provide kinetic energy recovery are disclosed. The gyroscopic system uses gyroscopic forces to maintain a vertical orientation at zero and low speeds, as well as maintain stability at all speeds. The gyroscopic forces are also be used to affect the bank angle of vehicles in turns, and to improve cornering by shifting forces to the inside wheels. The gyroscopes are also used to store kinetic energy, which is later used to accelerate the vehicle.
    Type: Application
    Filed: November 28, 2013
    Publication date: May 28, 2015
    Applicant: Thrustcycle Enterprises LLC
    Inventor: Clyde Igarashi
  • Publication number: 20150020616
    Abstract: This invention provides an improved Retail Display Cabinet with built in Gyroscope and servomotors to be primarily use at retail stores to showcase an item behind a transparent LCD. The Retail Display Cabinet has inside enough diffused light to better help the clear LCD display better quality images and/or videos. It has a built in gyroscope that identifies the position of the unit to determine the screen layout relevant to the aspect ratio of the screen to direct the lighting where is required. It also has built in servomotors to better show the product inside by rotating the product according to the pre-programmed commands.
    Type: Application
    Filed: April 16, 2014
    Publication date: January 22, 2015
    Applicant: Holografyx Canada Inc.
    Inventor: Alfonso Fabian de la Fuente Sanchez
  • Publication number: 20150007673
    Abstract: Spherical mechanical linkages may include a yoke defining a first axis and a second axis, a crank rotatably coupled to the yoke about the first axis; a deflecting member that defines a plane and that is coupled to the crank along a third axis, and a rocking frame slideably coupled to the yoke in the plane defined by the deflecting member and rotatably coupled to the yoke about the second axis. One or more components of the spherical mechanical linkage may be symmetric about an axis. A payload, such as a mirror or a camera, can be mounted on the linkage as part of a multi-axis tracker.
    Type: Application
    Filed: July 7, 2014
    Publication date: January 8, 2015
    Inventor: Donald E. Hultberg
  • Publication number: 20140366659
    Abstract: An anti-rolling gyroscopic stabilizer for boats provides a stationary frame fixed to the hull, an oscillating frame and a flywheel. The angular velocity of oscillation of the oscillating frame is limited by hydraulic dampers. Elastic return elements are coupled to the dampers and urge the oscillating frame so as to orient the axis of rotation of the flywheel towards a given angular position in which the gyroscopic device acts with maximum efficiency.
    Type: Application
    Filed: June 16, 2014
    Publication date: December 18, 2014
    Inventor: Roberto CHIESA
  • Publication number: 20140290398
    Abstract: A method comprises computing a metric based on the accelerometer signal to remove an acceleration due to gravity. A bandwidth of a gyroscope filter is set based on the accelerometer signal and the computed metric. The gyroscope filter uses a low-pass filter to filter a signal from the gyroscope.
    Type: Application
    Filed: November 14, 2013
    Publication date: October 2, 2014
    Applicant: Texas Instruments Incorporated
    Inventors: Deric W. Waters, Tarkesh Pande
  • Publication number: 20140260713
    Abstract: A gyroscope system comprises a MEMS gyroscope coupled to a drive system and a sense system. The drive system maintains the MEMS gyroscope in a state of oscillation and the sense system for receiving, amplifying, and demodulating an output signal of the MEMS gyroscope that is indicative of the rate of rotation. The gyroscope system further includes a phase-locked look (PLL) which receives a reference clock (REFCLK) from the drive system and produces a system clock (CLK). Finally, the gyroscope system includes a controller operating on the system clock sets an operating state of the drive system and the sense system and also controls a state of the PLL. One or more system state variables are maintained in a substantially fixed state during a protect mode thereby enabling rapid transitions between a low-power mode and a normal operating mode of the gyroscope system.
    Type: Application
    Filed: November 22, 2013
    Publication date: September 18, 2014
    Applicant: InvenSense, Inc.
    Inventors: Derek SHAEFFER, Stanley WANG
  • Publication number: 20140017083
    Abstract: System for stabilizing an offshore horizontal axis wind turbine having a tower, the system comprising sensors for generating signals representing detected movements of the tower, and gyroscopes. Each gyroscope has a spinning axis, an input axis and an output axis, and a flywheel rotatable about the spinning axis. The system further comprises an actuator for each gyroscope, said actuator being arranged with its related gyroscope in such a way that this actuator can apply a torque about the input axis of the gyroscope. The system also comprises a control unit for receiving the signals representing detected movements of the tower, and for providing the actuator with suitable control signals for said actuator to apply a torque about the related gyroscope input axis, said torque about the input axis producing a torque about the output axis of the same gyroscope that at least partly dampens the detected movements of the tower.
    Type: Application
    Filed: July 9, 2013
    Publication date: January 16, 2014
    Inventor: Isaac Pineda Amo
  • Patent number: 8485053
    Abstract: The illustrative embodiments provide a method and apparatus for stabilizing an electronic rack structure. In one embodiment the apparatus comprises an enclosure with a user interface panel. The apparatus also comprises a gyroscope, sensor system and controller attached within an enclosure. A sensor system associated with the gyroscope is capable of detecting a tilt of an electronic rack structure. A controller is also located within the enclosure and is capable of detecting the tilt of the electronic rack structure and controlling an orientation of the gyroscope to counter the tilt of the electronic rack structure in response to detecting the tilt. In another illustrative embodiment, a method for stabilizing an electronic rack structure is provided.
    Type: Grant
    Filed: December 30, 2008
    Date of Patent: July 16, 2013
    Assignee: International Business Machines Corporation
    Inventors: Jason Scott Lee, Thomas S. Mazzeo
  • Patent number: 8443683
    Abstract: Provided is a control moment gyroscope, in which a pair of momentum wheels are symmetrically disposed, thereby reducing torque noise and vibration, increasing output torque, and reducing its size. The control moment gyroscope includes a gimbal rim, a wheel frame having a first wheel frame located inside the gimbal rim and a second wheel frame having the same structure as the first wheel frame and symmetrically coupled with the first wheel frame, a first momentum wheel coupled to the first wheel frame, a second momentum wheel coupled to the second wheel frame corresponding to the first momentum wheel, a gimbal motor installed on an outer circumference of the gimbal rim and connected with first ends of the first and second wheel frames, and an angular velocity sensor installed on the outer circumference of the gimbal rim, connected with second ends of the first and second wheel frames.
    Type: Grant
    Filed: December 8, 2009
    Date of Patent: May 21, 2013
    Assignee: Korea Aerospace Research Institute
    Inventors: Seung-Wu Rhee, Jun-won Son, Seung Hyeon Kim
  • Publication number: 20120312095
    Abstract: A system for gyroscope dynamic motor amplitude compensation during startup comprises various program modules, including an a-priori motor amplitude module configured to generate an a-priori motor amplitude signal based on a model of gyroscope motor amplitude growth during startup; a steady state scale factor module configured to generate a steady state scale factor signal; and a dynamic motor amplitude compensation module configured to receive the a-priori motor amplitude signal, and the steady state scale factor signal. During startup, rate motion is sensed by the gyroscope and a sensed rate signal is output by the gyroscope. The dynamic motor amplitude compensation module receives a measured motor amplitude signal from the gyroscope, the a-priori motor amplitude signal, or a combination thereof, and outputs a time varying scale factor that is applied to the sensed rate signal to produce an accurate sensed rate from the gyroscope during the startup phase.
    Type: Application
    Filed: June 10, 2011
    Publication date: December 13, 2012
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Timothy J. Hanson, Mark W. Weber, Saul LaCoursiere
  • Patent number: 8322471
    Abstract: An apparatus and method are described for utilizing internally generated angular momentum for supplementing the propulsion of a mobile spherical vehicle capable of motion by rolling over terrain, thereby enabling such vehicles to climb steeper inclines and overcome larger obstacles. Torque generated by counter-rotating gyroscopes was used to supplement gravity generated torque produced by a pendulum drive propulsion system. Precession torque may be generated along a desired axis by changing the angular momentum of the gyroscopes while leaving its magnitude unaffected.
    Type: Grant
    Filed: November 16, 2009
    Date of Patent: December 4, 2012
    Inventor: Gregory C. Schroll
  • Patent number: 8312782
    Abstract: A self-contained momentum control system (MCS) for a spacecraft is provided for small satellites. The MCS features a miniaturized gyroscopic rotor with a rotational speed in excess of 20,000 RPM. The MCS includes at least three control moment gyroscopic mechanical assemblies (CMAs) rigidly mounted within a single enclosure, where each CMA mounted in an orientation whereby the longitudinal axis of each CMA is either orthogonal to every other CMA or is parallel to another CMA but in the opposite orientation. In order to further reduce the size of the MCS, an electronics package that is configured to interface command and control signals with and to provide power to the CMAs is included within the MCS enclosure. A plurality of shock isolation devices are used to secure each of the CMAs to the enclosure in order to reduce the launch load upon the CMAs thereby allowing the use of smaller rotor spin bearings. The MCS enclosure surrounding the CMAs and support structure is hermetically sealed.
    Type: Grant
    Filed: December 16, 2009
    Date of Patent: November 20, 2012
    Assignee: Honeywell International Inc.
    Inventors: Brett McMickell, Paul Buchele, Gary Lynwood Gisler, James Andrus
  • Patent number: 8214107
    Abstract: A vehicle behavior control apparatus includes a rotary body formed as a part of a power plant installed in a vehicle, and a shaft deflection unit that sets a vehicle behavior target value for obtaining a target vehicle behavior, and deflects a direction of a rotary shaft of the rotary body relative to a vehicle body in accordance with the vehicle behavior target value. Thus, the vehicle behavior can be controlled appropriately by using a pre-existing vehicle constitutional component such as an engine or a motor as the rotary body, and using a gyro moment generated by deflecting the direction of the rotary shaft of the rotary body.
    Type: Grant
    Filed: April 1, 2009
    Date of Patent: July 3, 2012
    Assignee: Toyota Jidosha Kabushiki Kaisha
    Inventor: Hirofumi Sato
  • Patent number: 8205514
    Abstract: A control moment gyroscope (CMG) is provided for deployment on a spacecraft. The CMG includes a stator housing, an inner gimbal assembly disposed in the stator housing, and a torque motor coupled to the stator housing and at least partially disposed around an intermediate portion of the inner gimbal assembly. The torque motor is configured to rotate the inner gimbal assembly about a gimbal axis.
    Type: Grant
    Filed: January 18, 2008
    Date of Patent: June 26, 2012
    Assignee: Honeywell International Inc.
    Inventors: Carlos J. Stevens, Stephen E. Fiske
  • Patent number: 8127631
    Abstract: A rotor assembly is provided for deployment within the inner gimbal assembly of a control moment gyroscope (CMG). In one embodiment, the rotor assembly includes a rotor shell, a rotor shaft fixedly coupled to the rotor shell, and a rotor rim. The rotor rim includes an annular body and a strain relief member. A first end portion of the strain relief member is fixedly coupled to the annular body, and a second end portion of the strain relief member is fixedly coupled to the rotor shell to form a rim-shell joinder interface. The strain relief member has a flexibility sufficient to reduce the mechanical stress experienced by the rim-shell joinder interface during operation of the CMG.
    Type: Grant
    Filed: September 17, 2008
    Date of Patent: March 6, 2012
    Assignee: Honeywell International Inc.
    Inventors: Gary Lynwood Gisler, Porter Davis, Roger Nagel, Dennis Wayne Smith
  • Publication number: 20110309191
    Abstract: A method of de-saturating a control moment gyroscope that leverages a torque on an aircraft that is generated by airflow over the aircraft. As an aircraft navigates through an airspace, the aircraft may destabilize and reorient to form a sideslip angle that forms the airflow torque on the aircraft. The control moment gyroscope may be de-saturated into a neutral position that in turn exerts a torque on the aircraft that counters the airflow torque. A scissor pair of first and second control moment gyroscopes can be used for generating a torque in a single plane.
    Type: Application
    Filed: June 17, 2010
    Publication date: December 22, 2011
    Applicant: LOCKHEED MARTIN CORPORATION
    Inventors: Paul D. McClure, Kenneth M. Dorsett
  • Publication number: 20110209568
    Abstract: An inner gimbal assembly is provided for use in a control moment gyroscope assembly and of the type that includes a stator housing and a spin motor disposed within the stator housing and on a shaft.
    Type: Application
    Filed: February 26, 2010
    Publication date: September 1, 2011
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventor: Jane Anderson
  • Patent number: 7878276
    Abstract: An ambulatory vehicle having legs and configured for transporting a load is disclosed. The ambulatory vehicle includes a load that is able to shift the center of gravity of the ambulatory vehicle along a transverse axis and a longitudinal axis of a beam assembly. Additionally, leg assemblies of the ambulatory vehicle are configured to exchange places along the length of the beam assembly. Further, the vehicle is able to perform a number of gaits including a slow stable gait and faster dynamic gaits comprising striding, trotting, and bounding. The ambulatory vehicle is able to navigate rough terrain and steep slopes and navigate submerged.
    Type: Grant
    Filed: March 30, 2009
    Date of Patent: February 1, 2011
    Inventor: H. Phillip Limbacher, Jr.
  • Publication number: 20100320330
    Abstract: A self-contained momentum control system (MCS) for a spacecraft is provided for small satellites. The MCS features a miniaturized gyroscopic rotor with a rotational speed in excess of 20,000 RPM. The MCS includes at least three control moment gyroscopic mechanical assemblies (CMAs) rigidly mounted within a single enclosure, where each CMA mounted in an orientation whereby the longitudinal axis of each CMA is either orthogonal to every other CMA or is parallel to another CMA but in the opposite orientation. In order to further reduce the size of the MCS, an electronics package that is configured to interface command and control signals with and to provide power to the CMAs is included within the MCS enclosure. A plurality of shock isolation devices are used to secure each of the CMAs to the enclosure in order to reduce the launch load upon the CMAs thereby allowing the use of smaller rotor spin bearings. The MCS enclosure surrounding the CMAs and support structure is hermetically sealed.
    Type: Application
    Filed: December 16, 2009
    Publication date: December 23, 2010
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Brett McMickell, Paul Buchele, Gary Lynwood Gisler, James Andrus
  • Patent number: 7854177
    Abstract: A precessional device having independent control of the output torque generated by the device and the oscillation rate of the device is disclosed. The device comprises a rotor supported by an axle wherein the ends of the axle are supported by a circular race. The circular race is rotatable, and may be driven by a motor or other means, thereby controlling the oscillation rate of the device independently of the output torque arising from the rotation rate of the rotor. The motor may be controlled by a control program that adjusts the rotation rate of the circular race to modify the shape of the resistance curve.
    Type: Grant
    Filed: May 22, 2007
    Date of Patent: December 21, 2010
    Inventor: Peter Winston Hamady
  • Patent number: 7840369
    Abstract: An apparatus correcting a bias of a gyroscope that is mounted on a mobile robot and that measures an angular velocity of the mobile robot. The apparatus includes: at least one encoder respectively measuring a traveling velocity of a respective at least one wheel of the mobile robot; a modeling unit calculating an angular velocity of the mobile robot by using the measured traveling velocity; a bias presuming unit determining a confidence range by using difference values between the calculated angular velocity and the measured angular velocity, and calculating a presumed bias by using a value in a confidence range among the difference values; and a bias removing unit removing the presumed bias from the measured angular velocity.
    Type: Grant
    Filed: July 5, 2007
    Date of Patent: November 23, 2010
    Assignee: Samsung Electronics Co., Ltd.
    Inventors: Hyoung-ki Lee, Ki-wan Choi, Dong-yoon Kim, Seok-won Bang
  • Publication number: 20100263463
    Abstract: A stabilization apparatus and a method for controlling stability of a suspended platform are described. System includes pivotally mounted gyro with an axis of rotation substantially orthogonal to the suspended platform's plane and adapted with the use of servos to convert precession of the gyro into a tilt of the platform. Described stabilization apparatus works in combination with the platform's main propulsion system. Apparatus is capable of providing high level stability for pitch, roll and yaw angles. Platform's orientation control can be optimized by changing modes of operation to control at any time any two of three angles defining position of the suspended platform. It would be advantageous to use such stabilized suspended platform as a camera pod and also in the flying models industry. Idea can be accommodated in the personal transportation vehicles, robotic vehicles both in airspace and outer space.
    Type: Application
    Filed: June 6, 2007
    Publication date: October 21, 2010
    Inventor: Zbigniew Janosik
  • Patent number: 7805226
    Abstract: A control system for adjusting the attitude of a spacecraft comprises a set of control moment gyroscopes (CMGs) configured to allow null space maneuvering. The control system further comprises a momentum actuator control processor coupled to the set of CMGs and configured to determine a mandatory null space maneuver to avoid singularities and determine an optional null space maneuver to increase available torque. The mandatory null space maneuver can be calculated based upon certain gimbal angles, and can be implemented by augmenting the inverse-Jacobian control matrix.
    Type: Grant
    Filed: September 29, 2006
    Date of Patent: September 28, 2010
    Assignee: Honeywell International Inc.
    Inventors: Brian J. Hamilton, Brian K. Underhill
  • Publication number: 20100162835
    Abstract: The illustrative embodiments provide a method and apparatus for stabilizing an electronic rack structure. In one embodiment the apparatus comprises an enclosure with a user interface panel. The apparatus also comprises a gyroscope, sensor system and controller attached within an enclosure. A sensor system associated with the gyroscope is capable of detecting a tilt of an electronic rack structure. A controller is also located within the enclosure and is capable of detecting the tilt of the electronic rack structure and controlling an orientation of the gyroscope to counter the tilt of the electronic rack structure in response to detecting the tilt. In another illustrative embodiment, a method for stabilizing an electronic rack structure is provided.
    Type: Application
    Filed: December 30, 2008
    Publication date: July 1, 2010
    Applicant: INTERNATIONAL BUSINESS MACHINES CORPORATION
    Inventors: Jason Scott Lee, Thomas S. Mazzeo
  • Patent number: 7694595
    Abstract: The resonator comprises a shell 1 a having a pole 2 held by a support rod 3, the shell having an annular edge 4 defined by an inside surface 5 and an outside surface 6 that are geometrically similar and that extend around a common axis of revolution R, the inside surface and the outside surface being offset relative to each other along the axis of revolution in such a manner that the shell presents a thickness E along the annular edge 4 that is greater than the thickness e that it presents in the vicinity of the pole 2.
    Type: Grant
    Filed: June 28, 2004
    Date of Patent: April 13, 2010
    Assignee: Sagem Defense Securite
    Inventors: Michel James, Alain Jeanroy
  • Publication number: 20100044517
    Abstract: An attitude control system for a spacecraft is disclosed that includes a scissored pair of control moment gyroscopes for delivering an output torque to the spacecraft along a an output axis, wherein each gyroscope has a spin motor for spinning a rotor about a rotor axis and a gimbal torque motor for rotating the rotor about a gimbal axis, and wherein the system includes a generator for extracting kinetic energy from the rotors during rotor deceleration to power the gimbal torque motors of the gyroscopes.
    Type: Application
    Filed: April 18, 2007
    Publication date: February 25, 2010
    Applicant: Ithaco Space Systems, Inc.
    Inventors: William E. Bialke, Eric Stromswold
  • Publication number: 20100043577
    Abstract: A controlled relative motion system having a base support, an output structure and a plurality of securing links each rotatably connected at a first end thereof to a selected one of the base support and the output structure with a circumferential motion pair of those securing links having each member thereof rotatably connected at an opposite second end thereof to that remaining one of the base support and the output structure so as to have the second end of each member rotate in a corresponding rotation plane. These second ends also rotate about a common symmetry rotation axis perpendicular to the rotation planes. In addition, there is a force imparting member that is coupled to a selected coupling one of said first and second ends of a selected one of said circumferential motion pair of securing links, and is capable of directing said coupling end to rotate.
    Type: Application
    Filed: June 4, 2009
    Publication date: February 25, 2010
    Applicant: Ross-Hime Designs, Inc.
    Inventor: Mark E. Rosheim
  • Publication number: 20100000349
    Abstract: A control moment gyroscope (CMG) is provided for deployment on a spacecraft. The CMG includes a stator housing, an inner gimbal assembly disposed in the stator housing, and a torque motor coupled to the stator housing and at least partially disposed around an intermediate portion of the inner gimbal assembly. The torque motor is configured to rotate the inner gimbal assembly about a gimbal axis.
    Type: Application
    Filed: January 18, 2008
    Publication date: January 7, 2010
    Applicant: HONEYWELL INTERNATIONAL, INC.
    Inventors: Carlos J. Stevens, Stephen E. Fiske
  • Patent number: 7554283
    Abstract: Disclosed is a non-reaction torque drive which can be called Reaction Free Drive or suspended support comprising: a Rotor, a Stator, two gyroscopes which are placed in side two frames, two high speed electro motors which rotate the two gyroscopes, and four 24v DC magnets which are used as actuators. The Drive not only conveys the torque to the output shaft, but also it removes a large percentage of reaction torque (about 95%) and does not pass the torque to its shell and support.
    Type: Grant
    Filed: June 14, 2007
    Date of Patent: June 30, 2009
    Inventor: Shahriar Yazdani Damavandi
  • Publication number: 20090120217
    Abstract: A rotor assembly includes a shaft; a mass; and a plurality of adjustable struts. The struts have a first end coupled to the shaft and a second end coupled to the mass such that the mass is movable with respect to the shaft.
    Type: Application
    Filed: November 13, 2007
    Publication date: May 14, 2009
    Applicant: HONEYWELL INTERNATIONAL, INC.
    Inventors: Timothy A. Hindle, M. Brett McMickell
  • Patent number: 7443257
    Abstract: A control system for a mechanical oscillator having a sinusoidal drive signal with a frequency that is a fractional multiple of a frequency of a signal of the mechanical oscillator. The drive signal may be in phase and in registration with the signal from the mechanical oscillator. A sense signal may be picked off from the oscillator and be demodulated to obtain a parameter sensed by the oscillator. The drive signal to the oscillator may be selected or blanked out while receiving and demodulating the sense signal.
    Type: Grant
    Filed: April 26, 2005
    Date of Patent: October 28, 2008
    Assignee: Honeywell International Inc.
    Inventor: Nick Anthony Demma
  • Publication number: 20080156126
    Abstract: Gyroscopic Torque Induced Unidirectional Engine is a combination of five engines with a center bi-directional torque motor controlling torque speed, direction and timing of both upper and lower pair-sets of Gyro engines attached to center motors upper and lower drive axles. By electronically manipulating the power to the bi-directional torque motor and the gyros', the force factors are controlled between the upper and lower sets. With the first phase of upper gyros operations repeated by the second phase of lower gyros inducing torques speeds and directions 180 degrees out of phase with the upper gyros. Timing is synchronized for gyros to support one another through its push-reach, pull-reach, “crawl” through space like a twisting caterpillar to obtain an overall combined total engine thrust in a single direction overcoming accelerated Gravity's weight plus POWER to create engine speed in any of the controlled directions.
    Type: Application
    Filed: July 11, 2005
    Publication date: July 3, 2008
    Inventors: Robert Monte Prichard, Robert Kraft McClelland
  • Patent number: 7383747
    Abstract: The present invention is a combination of three interconnected gyroscopic ring-like rotating masses, with each of the three ring-like masses being configured to rotate in various planes, depending on the desired orientation. Regardless of the orientation of the three rings, each of the three interconnected rotating masses will share substantially the same center of gravity and generate a separate yet interactive kinetic energy and angular momentum in each of the three planes, thereby providing resistance to rotational forces from external sources. This is known as “equal force presence.” Additionally, a series of pedestal supports for supporting the three ring-like masses is disclosed.
    Type: Grant
    Filed: October 16, 2006
    Date of Patent: June 10, 2008
    Assignee: Ganid Productions, LLC
    Inventor: Raymond Kelly Tippett
  • Publication number: 20080047375
    Abstract: According to an aspect of the present invention, there is provided an autonomous mobile apparatus including a movable body, a control moment gyro that generates a torque, a gyro unit that pivotably supports the control moment gyro about a first axis and a gimbal that pivotably supports the gyro unit about a second axis and is pivotable to the movable body about a third axis that is different from the second axis.
    Type: Application
    Filed: August 20, 2007
    Publication date: February 28, 2008
    Applicant: KABUSHIKI KAISHA TOSHIBA
    Inventor: Takafumi Sonoura
  • Publication number: 20080022790
    Abstract: An apparatus correcting a bias of a gyroscope that is mounted on a mobile robot and that measures an angular velocity of the mobile robot. The apparatus includes: at least one encoder respectively measuring a traveling velocity of a respective at least one wheel of the mobile robot; a modeling unit calculating an angular velocity of the mobile robot by using the measured traveling velocity; a bias presuming unit determining a confidence range by using difference values between the calculated angular velocity and the measured angular velocity, and calculating a presumed bias by using a value in a confidence range among the difference values; and a bias removing unit removing the presumed bias from the measured angular velocity.
    Type: Application
    Filed: July 5, 2007
    Publication date: January 31, 2008
    Applicant: SAMSUNG ELECTRONICS CO., LTD.
    Inventors: Hyoung-ki Lee, Ki-wan Choi, Dong-yoon Kim, Seok-won Bang
  • Patent number: 7225524
    Abstract: Method for fabricating a gyroscope including: fabricating a SMS wafer where a first wafer, a metal film, and a second wafer are sequentially stacked; forming a cantilever or a bridge shaped-structure on the relevant portion of the first wafer through the photolithography process; attaching to the surface of the first wafer, a first cap made of glass and having a predetermined space for sealing the movable structure in a vacuum state; separating and removing the metal film and the second wafer from the first wafer; and attaching to the backside of the first wafer, the second cap which is structurally and materially symmetric to the first cap. The SMS wafer is fabricated by depositing the metal film on the second wafer and bonding the first wafer on the metal film using metal paste or material of polymer series. With lower material costs, improvements in performance and characteristics can be achieved.
    Type: Grant
    Filed: December 3, 2004
    Date of Patent: June 5, 2007
    Assignee: Samsung Electronics Co., Ltd.
    Inventors: Moon-chul Lee, Hyung Choi, Seok-jin Kang
  • Patent number: 7181987
    Abstract: A precessional device having independent control of the output torque generated by the device and the oscillation race of the device is disclosed. The device comprises a rotor supported by an axle wherein the ends of the axle are supported by a circular race. The circular race is rotatable, and may be driven by, for example, a motor, thereby controlling the oscillation rate of the device independently of the output torque arising front the rotation rate of the rotor. The motor may be controlled by a control program that adjusts the rotation rate of the circular race to modify the shape of the resistance curve.
    Type: Grant
    Filed: May 2, 2003
    Date of Patent: February 27, 2007
    Inventor: Peter Winston Hamady
  • Patent number: 7051608
    Abstract: The gyroscopic actuator is a new device based on a mechanism designed to make us of the conservation of the kinetic momentum, so that it supplies a torque (momentum) to the platform where it is located. Thus it can orientate this platform in pitching, rolling or yawing, so that it achieves the attitude that a control system requires. Its scheduled use is in aeronautical fields (operation control in aeroplanes), automotion (stabilization of any type of land vehicle), naval (maneuvers and stabilization of naval platforms) and aerospace (satellite attitude control).
    Type: Grant
    Filed: October 11, 2002
    Date of Patent: May 30, 2006
    Assignee: Ingenieria, Diseno Y Analisis, S.L.
    Inventor: Juan José Guerrero
  • Patent number: 7014150
    Abstract: A momentum-control system for a spacecraft is disclosed. The momentum-control system comprises an attitude-control system. The attitude-control system receives data concerning a desired spacecraft maneuver and determines a torque command to complete the desired spacecraft maneuver. A momentum actuator control processor coupled to the attitude-control system receives the torque command. The momentum actuator control processor calculates a gimbal rate command comprising a range-space gimbal rate required to produce the torque command and a null-space gimbal rate required to maximize the ability to provide torque in the direction of a current torque. At least four control-moment gyros are coupled to the momentum control actuator control processor. Each of the control-moment gyros receives and executes the gimbal rate to produce the desired maneuver.
    Type: Grant
    Filed: July 30, 2004
    Date of Patent: March 21, 2006
    Assignee: Honeywell International Inc.
    Inventors: Mason A. Peck, Brian J. Hamilton, Brian Underhill
  • Patent number: 6982538
    Abstract: An apparatus is described which reduces a time delay and a resultant phase shift in a gyroscope motor drive signal. The motor drive signal originates from a numerically controlled oscillator whose output is sampled at a predetermined rate. The apparatus includes a first element which upsamples the oscillator output signal samples and a band pass filter configured to receive an output from the first element and remove spectral components from the output of the first element. The apparatus further includes a third element which generates a tuning parameter, ??o, for tuning of the band pass filter and a scaling multiplier configured to normalize an output of the filter.
    Type: Grant
    Filed: September 6, 2002
    Date of Patent: January 3, 2006
    Assignee: Honeywell International Inc.
    Inventor: Stanley A. White
  • Patent number: 6907800
    Abstract: Gyrostabilizer methods and apparatus having simultaneously counter-revolving masses that do not require physical shafts or axles. The stabilizer can have dual counter-revolving concentric rings, or tracks filled with weights such as spherical balls, that are propelled in orbital fashion by fluid pressure or electromagnet propulsion. The rings can include rigid contiguous rings, such as metal, plastic, composites, and the like. Additionally, the rings can include liquids and/or gasses. Still furthermore, the rings can include flexible, bendable contiguous materials, such as chains and ropes. The concentric ring diameters can be a few inches to more than ten (10) feet. Without an axle or shaft the weight of the gyrostabilizer is shifted to the perimeter where most of the momentum is generated at a fraction of the weight of gyrostabilizers that spin on an axle. The gyrostabilizer can dampen unsteadiness such as tremors, vibrations, sway, pitch, roll, and yaw.
    Type: Grant
    Filed: May 26, 2003
    Date of Patent: June 21, 2005
    Inventor: William E. Inman
  • Patent number: 6789437
    Abstract: An apparatus and a method for controlling the path of oscillatory travel of a device within a two-axis system. A device, such as a camera, is held in a two axis gimbal system having motors for driving the azimuth and pitch axes. A two degree-of-freedom gyroscope is fixed to the case of the device. A first derivative circuit is interposed between a first input port for a loop for controlling device movement with respect to a first axis and a second input port for a loop for controlling device movement with respect to a second axis. Likewise, a second derivative circuit is interposed between the two input ports so that a periodic signal driving with respect to one axis generates a derivative function for driving with respect to the cross-axis. The cross axis signal is scaled to counteract the direct torquing of the gyro rotor that otherwise prevents smooth oscillatory slewing or scanning by the device.
    Type: Grant
    Filed: July 31, 2001
    Date of Patent: September 14, 2004
    Assignee: Northrop Grumman Systems Corporation
    Inventor: Stanley F. Wyse
  • Publication number: 20040118231
    Abstract: A disturbance-cancellation system and method is provided that facilitates the adaptive cancellation of periodic disturbances. The disturbance-cancellation system and method includes a pair of control moment gyroscopes (CMGs) arranged together as a scissored pair. The scissored pair of CMGs is used to create a periodic torque with a controllable amplitude and frequency. The periodic torque created by the CMGs is adaptively controlled to cancel out periodic disturbances in the system. The system and method creates a periodic torque with a controllable amplitude and frequency by rotating the inner-gimbal assemblies of the CMGs in opposite directions at substantially equal phase and angular velocity. Amplitude matching can be achieved by adjusting the rotor spin rate. The steady-state constant motion results in a periodic torque along the output axis of the scissored pair, while components of torque along axes orthogonal to this one cancel out.
    Type: Application
    Filed: December 19, 2002
    Publication date: June 24, 2004
    Inventor: Mason A. Peck
  • Patent number: 6742381
    Abstract: A damping performance evaluation apparatus for damping devices including: a support member detachably supporting a damping device in a state enabling the device to exhibit a damping effect thereof; a hammer member for applying oscillation force to the device caused by gravitational descent to strike the device; a double-strike preventing member for preventing the hammer member from dropping a second time due to rebound after initially striking the device, to prevent double-strike of the device by the hammer member; a vibration sensor installed at a vibration zone caused to vibrate through oscillation force applied by said hammer member, for outputting an electrical signal in response to vibration at the vibration zone; and a sensing member for sensing a vibration mode in the vibration zone on the basis of an output of said vibration sensor. A damping performance evaluation method is also disclosed.
    Type: Grant
    Filed: January 29, 2003
    Date of Patent: June 1, 2004
    Assignee: Tokai Rubber Industries, Ltd.
    Inventor: Hajime Maeno
  • Publication number: 20040089083
    Abstract: A system and method for measuring orientation of an object: In the illustrative embodiment,, the object is a ball (42) in a ball and socket type pointing and stabilization system. The novel system (40) includes an encoded pattern (46) applied to a portion of the surface of the ball (42), a pattern reader (44) which reads the pattern (46) off the ball (42) and outputs data representative of the pattern (46), and a processor (48) which decodes the data into orientation information. In the preferred embodiment, the pattern reader (44) is an electro-optical sensor, and the encoded pattern (46) includes a grid of dots (52) arranged in a first predetermined number of dot code cycles (58) wherein each dot code cycle (58) includes a second predetermined number of dots. The processor (48) includes an algorithm (100) which computes pitch, yaw, and roll angles from the pattern reader data.
    Type: Application
    Filed: November 12, 2002
    Publication date: May 13, 2004
    Inventor: Theodore B. Bailey
  • Publication number: 20040079178
    Abstract: The new gyroscopic device (gyro-dipole) has two gyroscopes with equal angular momentum (gyro-twins) set in a common case with precession axis's disposed parallel and engaged via gears allowing gyro-twins to precess synchronical but contrary.
    Type: Application
    Filed: October 28, 2002
    Publication date: April 29, 2004
    Inventor: Vladislav Vasilyevich Gorshkov
  • Publication number: 20030024333
    Abstract: An apparatus and a method for controlling the path of oscillatory travel of a device within a two-axis system. A device, such as a camera, is held in a two axis gimbal system having motors for driving the azimuth and pitch axes. A two degree-of-freedom gyroscope is fixed to the case of the device. A first derivative circuit is interposed between a first input port for a loop for controlling device movement with respect to a first axis and a second input port for a loop for controlling device movement with respect to a second axis. Likewise, a second derivative circuit is interposed between the two input ports so that a periodic signal driving with respect to one axis generates a derivative function for driving with respect to the cross-axis. The cross axis signal is scaled to counteract the direct torquing of the gyro rotor that otherwise prevents smooth oscillatory slewing or scanning by the device.
    Type: Application
    Filed: July 31, 2001
    Publication date: February 6, 2003
    Inventor: Stanley F. Wyse