A vibration measurement system comprises an image capturing apparatus, a distance measuring apparatus, a sensor that outputs a signal according to an inclination of the image capturing apparatus relative to the vertical direction, and a vibration measurement apparatus. The vibration measurement apparatus includes calculating an angle formed by the normal of an image capturing surface of the image capturing apparatus and the normal of the measurement target surface that the image capturing apparatus shoots, based on the signal output by the sensor, converting the image obtained that the image capturing apparatus shoots into an image that would be obtained were the normal of the measurement target surface coincident with the normal of the image capturing surface of the image capturing apparatus, using the calculated angle, and measuring vibration of the structure, using the converted image and the measured distance from the image capturing apparatus to the measurement target surface.

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 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.

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.

Method for measuring an angular velocity and/or position comprising: (a) receiving first and second detection signals regarding a vibration from primary and secondary resonance modes of a resonator; (b) implementing at least four control loops using first, second, third and fourth regulators, respectively; and (c) estimating said angular velocity and/or position, as a function of regulator outputs. The first regulator aims at minimizing the difference between the in-phase component of the first detection signal and the product, by a first coefficient C1 that is a function of the azimuthal angle ? in the orthogonal modal base of primary and secondary modes, of a setpoint vibration amplitude of the resonator. The third regulator aims at minimizing the difference between the in-phase component of the second detection signal and the product, by a second coefficient C2 that is a function of ? and the setpoint vibration amplitude. Also, associated gyroscope sensors.

There is provided a gyro vibrometer configured to detect vibration of a subject with high sensitivity. The gyro vibrometer includes a support body including an opening portion, a film disposed on the support body in which part of the film is located over the opening portion, and at least one gyro sensor disposed on a surface on the opening side of the film.

Feedback control circuitry includes rate limiter circuitry configured to generate a rate limited position command based on a position command for a controlled component and based on a speed command for the controlled component. The feedback control circuitry also includes error adjustment circuitry configured to apply a control gain to an error signal to generate an adjusted error signal. The error signal is based on position feedback and the rate limited position command, and the position feedback indicates a position of the controlled component. The feedback control circuitry further includes an output terminal configured to output a current command generated based on the adjusted error signal.