Abstract: A gyroscopic stabilizer configured to stabilize a surgical instrument relative to a patient includes a frame having a central axis and a hub configured to releasably couple with the surgical instrument. A first gyroscope assembly is coupled with a first frame portion and a second gyroscope assembly is coupled with a second frame portion. Each gyroscope assembly includes a gimbal pivotably coupled with the respective frame portion about a precession axis, a motor, and a rotor rotatably coupled with the motor about a spin axis perpendicular to the respective precession axis. Each gyroscope assembly is operable generate a torque in a torque plane that contains the respective spin axis and the respective precession axis. The torques are configured to resist rotation of the gyroscopic stabilizer relative to the patient about respective device axes that are perpendicular to the central axis and to one another.

Abstract: A suspended system with orientation control. The system may have a frame, a sign attached to the frame, a plurality of sensors, at least two thrusters, and a microcontroller operatively coupled to the plurality of sensors and the thrusters. The frame is configured to be suspended from a support, and the sign is configured to display a graphic. The plurality of sensors is configured to track an orientation of the frame. The thrusters are configured to adjust the orientation of the frame. Each of the thrusters may have an axis oriented in a direction perpendicular to the frame. The microcontroller is configured to receive a selected orientation of the frame, receive the current orientation of the frame from the sensors, compare the orientation of the frame with the selected orientation, and control the thrusters to adjust the orientation of the frame into the selected orientation.

Abstract: A method for detecting a payload on a carrier configured to support the payload includes obtaining a obtaining at least one motion characteristic of the carrier. The at least one motion characteristic is indicative of a coupling state between the carrier and the payload. The method further includes assessing the coupling state between the carrier and the payload based on the at least one motion characteristic. Assessing the coupling state between the carrier and the payload includes at least one of assessing whether the payload is coupled to the carrier or assessing whether the payload is correctly mounted at the carrier.

Abstract: Provided is a twin disc pump which includes split rod bearings for connecting pump discs to a drive shaft, and pedestal bearings that also receive the drive shaft. The split rod bearings can be disassembled without having to disassemble any portion of a housing of the pump. Accordingly, an operator can gain access to the split rod bearings, the pedestal bearings, and the drive shaft from above the pump without having to access the pump from below. The twin disc pump also includes a new attachment mechanism for connecting a top portion of the housing to an intermediate portion. The twin disc pump also includes a modified metal ring for improved leakage prevention and easier release. The twin disc pump may also be included within a system including a frame capable of locking the pump in different orientations.

Abstract: Method of servicing or maintaining a gyroscope of an anti-roll stabilizer onboard of a seacraft. The method comprising a step of providing a seacraft provided with an anti-roll stabilizer. The stabilizer comprises a gyroscope comprising a container housing a rotor including a flywheel and a flywheel shaft that is rotatably mounted within said container by means of two support devices placed inside said container and arranged to support a respective end of said flywheel shaft so as to allow the relative rotation of said shaft with respect to said container. The container comprises a base portion mounted on a suspension held by a frame of the anti-roll stabilizer so as to be able to oscillate around a first axis transverse with respect to a rotation axis of the flywheel shaft. The container further comprises two end portions removably connected to said base portion.

Abstract: Described is a system for supporting a camera, said camera being fixed on an articulated head which allows the homogeneous movement along axes Zpan and Ytilt, said articulated head being equipped with variable fluid dampening means and counterbalancing means, for annulling the weight of the camera when rotated about the Ytilt axis, aid system being equipped with a structure for the rotation of the camera about a third Xroll axis, said structure being interposed between said head, above the same, and said camera, below the same.

Abstract: A preformed foundation support for a vessel gyro-stabilization system, comprises at least three of a first side support, a second side support, a third side support, and a fourth side support. The side supports define an opening for accommodating at least a portion of a vessel gyro-stabilization system, and the side supports comprise a cuttable portion for custom fitting the preformed foundation support in a vessel. The preformed foundation support structure is installed in the vessel by cutting the cuttable portion of the preformed foundation support for custom fitting the preformed foundation support to the structure support of the vessel. The preformed foundation support structure can be manufactured as a molded fiberglass structure.

Abstract: A surgical instrument comprises a member configured for connection to an image guide defining an axis and being oriented relative to a sensor to communicate a signal representative of a position of the member. A stabilizer is aligned with the axis and configured to resist and/or prevent movement of the image guide from the orientation. Systems and methods are disclosed.

Abstract: An acquisition circuit for a vehicle or other system is provided. The system, for example, may include, but is not limited to a control moment gyroscope, and a fully differential ground isolated acquisition circuit communicatively connected to the control moment gyroscope and configured to acquire a differential data signal on the control moment gyroscope and output the differential data signal to at least one output node. The acquisition circuit may include, but is not limited to a ground reference correction circuit configured to recenter the differential data signal on at least one output node, and at least one ultra-high impedance output circuit coupled between the ground reference correction circuit and the input differential circuit.

Abstract: Disclosed is a spherical wheel motor including: a spherical rotor having freedom of rotation along surrounding magnetized directions; a stator formed in a dome shape enclosing the rotor and configured to form magnetization at various angles through a plurality of coils distributed therein, and impart the freedom of rotation to the rotor; and a driving unit configured to identify a position of the rotor, supply current to each coil of the stator according to the position of the rotor, and drive the rotor.

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.

Abstract: A motor having a compact and lightweight design may include a stator provided by a flexible printed circuit (flex circuit). The flex circuit may include a plurality of etched windings that provide coils for a plurality of motor phases. A printed circuit board of the motor may provide various device functions such as electrical commutation. The motor may be used in various applications such as a cooling fan for device electronics and gyroscopic applications.

Abstract: A motorized weapon gyroscopic stabilizer which creates a stabilizing effect for single shot, semi-automatic, and fully automatic weapons. The rotating mass that generates the gyroscopic stabilizing effect is the rotor of the motor. The motor is designed to allow the mass to rotate around the open core of the motorized weapon gyroscopic stabilizer. Because of its open core design the motorized weapon gyroscopic stabilizer allows the fired projectile to pass through it, or be mounted in line with the sighting mechanism allowing the target alignment—line of sight to pass through the motorized weapon gyroscopic stabilizer, or both.

Abstract: A gyroscopic device is described for providing rotation about at least one output axis and a method for providing rotation. A body (2) is mounted for a rotation about first (4), second (11), and third (16) axes. The first axis (4) is oriented with respect to the second axis (11) at an inclination angle. The second axis (11) and/or the third axis (16) constitute the at least one output axis of device. The rotation of the body (2) about the third axis (16) gives rise to a change in the inclination angle. A ram (15) applies a torque (21) to the body (2) about the third axis (16) in a sense of increasing inclination angle when the first axis (4) is at a selected inclination angle with respect to the second axis (11) which is greater than 0° and less than 90°. The rotation of the body (2) about the third axis (16) in a sense of decreasing inclination angle is limited such that the inclination angle of the first axis (4) with respect to the second axis (11) remains greater than 0 degrees and less than 90 degrees.

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. The inner gimbal assembly comprises a first spin bearing mounted to the shaft, and a bearing cartridge substantially surrounding the first spin bearing, the bearing cartridge having a first end partially defining a first end cavity, a second end partially defining a first intermediary cavity, and a bearing cartridge channel providing flow communication between the first end cavity and the first intermediary cavity.

Abstract: Disclosed is a combination of six substantially identical interconnected rotating masses, with a pair each of the rotating masses being configured to rotate in one of each of the three planes (X, Y, and Z). Regardless of the orientation of the six masses, each pair of the six interconnected rotating masses may 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.” In one embodiment, the rotating masses are ring-like masses. In alternative embodiment, the rotating masses are solid masses, similar to flywheels.

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.

Abstract: A combination motorized and propelled apparatus and moment imparting device is provided to improve the stability of the apparatus in motion with regard to pitch, roll and yaw. The moment imparting device uses one or more rotational members rotating around one or more axes to create a net rotational moment force around a desired axis of rotation. The moment imparting device is in communication with the motorized apparatus to translate that moment force to the motorized apparatus to improve stability or induce a desired rotation.

Abstract: Method and system for providing precise stabilization of a supporting structure for supporting at least one device used for aiming while the supporting structure is moving. MEMS gyroscope is employed for providing stabilization signals to driving means connected to said supporting structure for continuous stabilization adjustments of movements of the supporting structure.

Abstract: A sensor assembly includes a sound sensor, an image sensor, an acceleration sensor, and a gyroscope sensor. The sound sensor includes a substrate defining a first cavity, a diaphragm positioned on the substrate and covering the first cavity, a back plate covering the diaphragm and positioned on the substrate, and a capacitance. A first electrode layer is coated on the diaphragm and faces the first cavity. A second cavity is defined between the diaphragm and the back plate. A second electrode layer is coated on the back plate and faces the second cavity. The capacitance is electrically connected between the first and second electrode layers. The image sensor, the acceleration sensor, and the gyroscope sensor are positioned on the substrate.

Abstract: Disclosed is a combination of six substantially identical interconnected rotating masses, with a pair each of the rotating masses being configured to rotate in one of each of the three planes (X, Y, and Z). Regardless of the orientation of the six masses, each pair of the six interconnected rotating masses may 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. In one embodiment, the rotating masses are ring-like masses. In alternative embodiment, the rotating masses are solid masses, similar to flywheels.

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.

Abstract: Methods and systems are provided for attaching and detaching a payload device to and from, respectively, a gimbal system without requiring use of a mechanical tool. The gimbal system includes a gimbal assembly that includes a payload socket arranged to attach a payload device to the gimbal assembly. The payload socket is preferably arranged to allow any of a plurality of payload devices to attach to and detach from the payload socket without requiring use of a mechanical tool.

Abstract: An AGSS for an RC two-wheel model composed of a wheel body, a wheel frame received in the wheel body, a spindle inserted through the wheel frame, a transmission gear assembly mounted to the spindle, a flywheel assembly mounted to the spindle, and a unidirectional rotary assembly. The unidirectional rotary assembly includes a sleeve rotatably sleeved onto the spindle, and a unidirectional rotary member mounted to the sleeve. The sleeve has external annular teeth engaging the transmission gear assembly. The unidirectional rotary member is mounted in the flywheel assembly for driving unidirectional rotation of the flywheel assembly as the RC two-wheel model gets started and for disengaging from the flywheel assembly as the RC two-wheel model brakes, such that the flywheel idles to protect the internal parts of the RC two-wheel model from inertial collision.

Abstract: A clamp of less waste instruction method for an addition axis, which omits instructions for clamping and unclamping and working in response to those instructions, includes the steps of, at a stage of working a work piece with a tool, measuring a rotational torque generated by the working with respect to the addition axis coupled to a table which supports the work piece or a pallet having the work piece mounted thereon; and generating a clamp instruction to the addition axis when the rotational torque exceeds a predetermined reference value.

Abstract: An automatic transmission consisting of a planetary gear unit comprising in combination an input shaft (1), an input gear (2), a key planet gear (3), an output gear (4), an output shaft (5), a bearing planet gear (6), a rotating frame (7), a rotor (8), wherein the planet shaft is the rotor (8) having a certain inertia moment, so its revolving is equivalent to the precession of a gyroscope due to an external force wherein the precession-production external force is the load acting on the output shaft (5). Hence the revolutionary speed of the rotor (8) varies depending upon changes in the output load and the same holds true for the rotational speed of the output shaft (5), which makes the speed ratio spontaneously vary with changes in the outpot load. Accordingly, the transmission of the present invention operates at speed ratios spontaneously varying with changes in load, without any controlling operation.

Abstract: A torque converter comprises a stationary mount, input and output shafts, a primary frame (301) supported by the stationary mount for rotation about a primary axis and coupled for rotation with one of the input and output shafts (302,303), a secondary frame (50) supported by the primary frame (301) for rotation about a secondary axis perpendicular to the primary axis and coupled for rotation with the other of the input and output shafts, a plurality of flywheels (10) supported by the secondary frame (50) with their spin axes disposed at an angle to one another in the same plane, or in mutually parallel planes, and torsional springs acting between the flywheels and the secondary frame to cause the flywheels to oscillate in use, so as to effect a gyroscopic torque coupling between the primary and secondary frames.

Abstract: A demodulator is provided for demodulating an amplitude-modulated input signal defined by a carrier signal having a carrier frequency modulated by a modulating signal, the demodulator including an amplifier stage having a gain and structured to receive the amplitude-modulated input signal, and a gain control stage coupled to the amplifier stage and configured to vary the gain of the amplifier stage according to the carrier frequency of the carrier signal.

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.

Abstract: A torque amplifying device that is of centrifugal or gyroscopic type and has a unidirectional drive or drives. This device is used to control the body of a controlled object. The controlled object can be an airplane, helicopter, land vehicle, cargo handling mechanism, earth moving machine or maritime device or vehicle. The torque amplifying devices are designed so that they supply a torque (momentum) to the body of the controlled object where it is connected. Thereby, the orientation or weight distribution of the body is controlled. The orientation is achieved without resorting to the physical properties of the surrounding environment (ground, water or air). Thus, it can apply a torque to this body in pitch, roll and/or yaw, so that it achieves the position or weight distribution the control system is calling for. The duration of the torque can be unlimited, until the conditions that produce it are intentionally changed.

Abstract: A device for use with a gyroscopic stabilizer for use in an assembly that is moveably connected to a vehicle. The gyroscopic stabilizer has a gyroscope, a skew motor, and a skew motor velocity servo-control system. The gyroscopic stabilizer can control a skew of the assembly based on a torque signal to maintain the assembly in an intended position. The skew motor velocity servo-control system can control the skew motor. The skew motor can move the gyroscope. The gyroscope can provide the torque signal. The device comprises an assembly position determining system, a detector, a state estimator and an output portion. The assembly position determining system can generate an assembly position signal based on one of a position of the assembly, a position of the gyroscopic stabilizer, a position of the gyroscope, a position of the skew motor and a position of the skew motor velocity servo-control system.

Abstract: A gimbal assembly includes a gimbal mechanism, an electrical connector, and a flexible substrate. The gimbal mechanism is configured to rotate about a first rotational axis and a second rotational axis that is perpendicular to the first rotational axis. The electrical connector is coupled to, and mounted on, the gimbal mechanism. The flexible substrate is coupled to the electrical connector and is adapted to be coupled to an external circuit for electrically interconnecting the electrical connector and the external circuit.

Abstract: Methods and apparatus are provided for reorienting control moment gyros (CMGs) to compensate for CMG failure or change in spacecraft (S/C) mass properties or mission. An improved CMG comprises a drive means for rotating the CMG around an axis not parallel to the CMG gimbal axis. Releasable clamps lock the CMG to the spacecraft except during CMG array reorientation. CMGs arrays are combined with attitude sensors, a command module, memory for storing data and programs, CMG drivers and sensors (preferably for each CMG axis), and a controller coupling these elements. The method comprises determining whether a CMG has failed or the S/C properties or mission changed, identifying the working CMGs of the array, determining a new array reorientation for improved spacecraft control, unlocking, reorienting and relocking the CMGs in the array and updating the S/C control parameters for the new array orientation.

Abstract: The present technical solution provided allows it to meet the problem of keeping the direction given by the use of the stabilized element in the plane of the inertial space, irrespective of acting harmful torques, precessions of gyroscopes and turns in that plain of the movable object whereon the solution is used. This solution is based on forced creation of those precessions of two one-axis gyrostabilizers towards the opposite sides, connected with each other by the connection unit comprising the stabilized element. Since in the present solution use can be made of the gyroscope of low accuracy, then the solution provided can be implemented in the small-size version.

Abstract: A gyroscopic exercise device has a pair of handles attached to a housing. A user holds and rotates the handles along cone-like paths causing precession of a rotor, which is rotating about its spin axis, to provide resistance to the user. The device has an axle disc that holds ends of an axle of the rotor. The periphery of the axle disc and the ends of the rotor axle are within a circular race in the housing. A motor attached to the axle disc has a wheel for rotating the rotor about a spin axis by a temporary supply of power from included batteries in one of the handles. The batteries are in between two opposite springs in one of the handles and normally biased away from an electrical contact until the user pushes them through an end pin to overcome the bias.

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.

Abstract: An exoatmospheric device comprises an inertial measurement unit comprising a spin axis gyroscope adapted to obtain data regarding angular rotation of the exoatmospheric device about a spin axis, and at least one off-spin axis gyroscope adapted to obtain data regarding angular oscillation of the spin axis. The exoatmospheric device further comprises a processing unit coupled to the inertial measurement unit and adapted to detect attitude error by analyzing correlations between the measured rotation about the spin axis and the measured angular oscillation of the spin axis.

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.

Abstract: The present invention relates to a reaction wheel assembly and fiber optic gyro device. The device includes a reaction wheel assembly having a reaction wheel assembly housing, a fiber optic gyro coil integrated with the reaction wheel assembly housing, and a fiber optic gyro electronics integrated with the reaction wheel assembly housing. The fiber optic gyro coil may be wound around the reaction wheel assembly housing. The gyro coil may also be located within the reaction wheel assembly housing.

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).

Abstract: A gyroscopic roll stabilizer for a boat. The stabilizer includes a flywheel, a flywheel drive motor configured to spin the flywheel about a spin axis, an enclosure surrounding a portion or all of the flywheel and maintaining a below-ambient pressure or containing a below-ambient density gas, a gimbal structure configured to permit flywheel precession about a gimbal axis, and a device for applying a torque to the flywheel about the gimbal axis. The flywheel, enclosure, and gimbal structure are configured so that when installed in the boat the stabilizer damps roll motion of the boat. Preferably, the flywheel drive motor spins the flywheel at high tip speeds.

Abstract: A system is disclosed for using camera attitude sensors with a camera. A camera assembly includes a tripod base, a tripod head interface mounted on the tripod base, a tripod head mounted on the tripod head interface and a camera mounted on the tripod head. The tripod head enables the camera to pan and tilt. The system also includes a first optical encoder for detecting the amount that the camera has been panned and a second optical encoder for detecting the amount that the camera has been tilted. Two inclinometers are mounted on the tripod head interface to measure attitude of the tripod head. Two gyroscopes (“gyros”) are mounted on the camera assembly. Data from the encoders, gyros and inclinometers are packaged and sent to graphics production equipment to be used for enhancing video captured by the camera.

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.

Abstract: A dynamic unbalance compensation system that compensates for dynamic unbalance of a rotating assembly on a vehicle, such as a spacecraft, to compensate for the presence of a dynamic unbalance moment. The system includes a vehicle, such as a spacecraft, a rotational assembly mounted on the vehicle and rotatable about an axis of rotation relative to the vehicle, and one or more momentum devices mounted on the rotational assembly and generating a momentum vector component perpendicular to the axis of rotation. The one or more momentum devices generate a compensation torque during spinning of the rotational assembly so as to compensate for dynamic unbalance of the rotational assembly.

Abstract: Apparatus, methods, and systems are disclosed for removing stress on gyroscopes during acrobatic flight and for causing gyroscopes to fail in a controlled manner during testing and training. A valve for protecting a pneumatic-gyroscopic aircraft instrument comprises a body and a seat having a selective interrupter and an arm. The selective interrupter is positioned inside the body and can rotate inside the body. A method for protecting a pneumatic-gyroscopic aircraft instrument comprises allowing a pneumatic flow to the instrument during flight, and then, redirecting, selectively, without interrupting the pneumatic flow to the instrument. A system for protecting a pneumatic-gyroscopic aircraft instrument comprises a means for allowing a pneumatic flow to the instrument during flight, and a means for selectively redirecting, without interrupting, the pneumatic flow to the instrument without undue stress on the driver source.

Abstract: A transmission is provided which includes a fixed housing or support, an input part moveable relative to the support and a torque shaft, a first one-way clutch between the torque shaft and the driven shaft, linkage elements rotatable about the axis of rotation of the driven shaft under the influence of the input parts and an inertial body mounted on the linkage elements to be cyclically angularly deflected in response to the input part, the reaction forces generated by the inertial body as it cyclically deflected being applied to the torque shaft as a positive and negative torque and the torque shaft being connected over a second one-way clutch opposite to the first one-way clutch either to the support or to the driven shaft over a rotation reversal system whereby the driven shaft can be rotated by the torque shaft in one sense of rotation only.

Abstract: In the case of a navigation computer of a motor vehicle, the housing of a gyroscope is arranged in the housing wall of the navigation computer such that the angle of the gyroscope can be adjusted. For this purpose, the invention provides that the housing of the gyroscope has two mutually opposite spring tongues (5, 6) which are directed upward and simultaneously radially outward from the top side of the gyroscope, and the housing wall has a holder (2) with two opposite passages (7, 8) for pushing through the spring tongues (5, 6) and, adjacent in each case to the passages (7, 8), a rotary member (9, 10) each in the shape of a circular arc as bearing surface for the spring tongues (5, 6).

Abstract: Appliance such as a two-legged robot made up of a system giving ground support and an upper body (30), equipped with a gyroscopic rotor wheel (31) which acts as a fulcrum to balance the appliance when positioned in reverse pendulum. A satisfactory equilibrium is guaranteed, thereby releasing from this function the command system in charge of robot locomotion or pathway.

Abstract: A system for balancing two-wheeled vehicles when approaching rest or when at rest is provided. The system includes a spinning gyro rotor which is precessed upon the sensing of incipient tipping of the vehicle when the vehicle is at rest or approaching rest for generating a force for preventing such tipping. The system may be packaged in a small module that can be mounted on existing two-wheeled vehicles.

Abstract: The present invention is directed to an infinitely variable transmission system that includes a gyroscope and a rotatable gear assembly to translate torque from an input power shaft to an output power shaft.