Embodiments of a spherical momentum control device are provided. In one embodiment, the spherical momentum control device includes a housing assembly bounding a cavity, a rotor support axle disposed within the cavity, and a spherical bearing interface formed between the rotor support axle and the housing assembly. The spherical bearing interface facilitates rotation of the rotor support axle within the cavity about three orthogonal axes transecting substantially at the cavity center point. A rotor is mounted to the rotor support axle (e.g., through precision bearings) for rotation about a spin axis. The spherical bearing interface can assume any form for facilitating rotation of the rotor support axle about the orthogonal axes including, for example, a low friction plane bearing interface. In one embodiment, the spherical bearing interface includes rolling element bearings embedded in the cavity walls or embedded in enlarged end caps forming part of the rotor support axle.

The present invention relates to attitude control and, in particular, to control of the attitude of a space platform. The space platform may take the form of or be part of a satellite and/or a spacecraft. An aspect of the present invention concerns the use, in an attitude control system, of several control moment gyroscopes with limited gimbal revolutions. Another aspect of the present invention concerns an improved logic for controlling a control moment gyroscope assembly of an attitude control system.

A gyro-stabilizer for a two-wheeled single-track vehicle, preferably a motorcycle, applicable in several driving modes, is configured in the form of a gyroscope in a gimbal mount, an outer ring of which is connected by a two-way axial pivot joint to the vehicle frame, wherein the axis of said joint is oriented along the longitudinal axis of the vehicle; an inner ring of the gimbal mount is connected by a two-way axial pivot joint to the outer ring; and a spin axis of the gyroscope is connected by a two-way axial pivot joint to the inner ring, wherein the axes of all three pivot joints are mutually perpendicular, and wherein the gyro-stabilizer has a means for locking rotation of the outer ring about the axis of the pivot joint between said outer ring and the frame of the vehicle. The gyro-stabilizer is disposed on the rear wheel swingarm and has a means for locking rotation of the inner ring about the axis of the pivot joint between the inner ring and the outer ring.

A gyro-stabilizer for a two-wheeled single-track vehicle, preferably a motorcycle, applicable in several driving modes, is configured in the form of a gyroscope in a gimbal mount, an outer ring of which is connected by a two-way axial pivot joint to the vehicle frame, wherein the axis of said joint is oriented along the longitudinal axis of the vehicle; an inner ring of the gimbal mount is connected by a two-way axial pivot joint to the outer ring; and a spin axis of the gyroscope is connected by a two-way axial pivot joint to the inner ring, wherein the axes of all three pivot joints are mutually perpendicular, and wherein the gyro-stabilizer has a means for locking rotation of the outer ring about the axis of the pivot joint between said outer ring and the frame of the vehicle. The gyro-stabilizer is disposed on the rear wheel swingarm and has a means for locking rotation of the inner ring about the axis of the pivot joint between the inner ring and the outer ring.

A gyro sensor includes: a substrate; a first drive section; and a first detection section and a second detection section that detect angular velocity. The first detection section includes a first movable body including a first movable electrode that vibrates by vibration of the first drive section and is displaced in response to the angular velocity, and a first fixed electrode fixed to the substrate and facing the first movable electrode. The second detection section includes a second movable body including a second movable electrode that vibrates by vibration of the first drive section and is displaced in response to the angular velocity, and a second fixed electrode fixed to the substrate and facing the second movable electrode. The first movable body and the second movable body are coupled together by a first coupling section.

The present invention relates, in general, to attitude control and, in particular, to control of the attitude of a space platform, conveniently of a satellite and/or a spacecraft. In detail, an aspect of the present invention concerns the use, in an attitude control system, of several Control Moment Gyroscopes with limited gimbal revolutions. Moreover, another aspect of the present invention concerns an improved logic for controlling a Control Moment Gyroscope assembly of an attitude control system.

A position sensing system comprises a position sensor having an accelerometer and a gyroscope, an alarm, and a controller configured to receive data from the position sensor and activate the alarm according to alarm management instructions stored in a memory. In some embodiments, the alarm instructions include a snooze option to allow the user/patient to temporarily deactivate the alarm. The controller is communicably linked to a remote display device configured to display the orientation of the user's body part.

An apparatus integrates two gyroscopes into one unit, allowing their forces to unite in such a manner that they work together in balanced harmony. This is achieved by applying a precessional propulsion method of operation to the gyroscopic balance unit to harness balance and direct gyroscopic forces so they flow together and work as a team, developing dual-balanced gyroscopic precession that in turn generates balanced propulsion.

This measurement device for measuring the angular velocity or acceleration of a two-wheel vehicle, is provided with a main detection unit which detects the three-axis angular velocity or three-axis acceleration, a support unit which can support the main detection unit on the body of the two-wheel vehicle, and a correction unit which cancels the lean of the body to the left and right in the main detection unit.

A gyro sensor apparatus includes a driving section that supplies a driving signal, which is for vibrating a sensing element of a vibration-type gyro sensor in a drive axis direction, to the sensing element, and a processing unit that receives a first vibration signal having an amplitude proportional to a driving vibration amplitude, which is an amplitude of vibration in the drive axis direction of the sensing element and a second vibration signal having an amplitude proportional to Coriolis force generated in the sensing element due to an angular velocity of the sensing element. The processing unit is configured to calculate a ratio of Coriolis force to the driving vibration amplitude based on the first vibration signal and the second vibration signal and output a result of the calculation as a result of detection of the angular velocity of the sensing element.