Abstract:
Packaging techniques for planar resonator gyroscopes, such as disc resonator gyroscopes (DRGs) are disclosed. A gyroscope die may be attached to its package substrate on a central disc area that is inboard of its embedded electrodes. This configuration eliminates contact of the die with the package substrate beneath the embedded electrodes allowing the internal electrode support structure to expand or contract freely without stress as its temperature changes. The central attachment can also be used diminish the package temperature gradients on the periphery of the die, if the thermal conductivity of the central disc attachment material is higher than the package substrate. Temperature gradients across the resonator also lead to thermoelastic damping asymmetry and rate drift. In addition, the electrical connections to the die may be formed by vertical vias within the central disc attachment area or by thin wirebonds to peripheral I/O pads on the gyro chip.
Abstract:
One embodiment is a micro hemispheric resonator gyro having: a plurality of pickoff and forcer electrodes; a hemispheric resonator; a guard ring having first and second opposed sides, the guard ring containing the plurality of pickoff and forcer electrodes, and the hemispheric resonator; a top cover operatively coupled to the first side of the guard ring; and a bottom cover operatively coupled to the second side of the guard ring; wherein the plurality of pickoff and forcer electrodes, the hemispheric resonator, the guard ring, the top cover and the bottom cover form a micro hemispheric resonator gyro.
Abstract:
A gyrocompass has a gyrosphere which incorporates a rotor and floats in a liquid tank filled with an electrolyte, and a plurality of electrodes which are disposed in the gyrosphere and the liquid tank, and are respectively opposed through the electrolyte, wherein at least one circuit which supplies electric power to the rotor involves the electrodes, and the plurality of the electrodes includes a first belt-shaped electrode disposed in an equatorial portion of the gyrosphere, the first belt-shaped electrode is formed of a metal which is corrosion-resistant and is a good conductor, and an insulating film is formed on a portion of a surface of the first belt-shaped electrode.
Abstract:
The invention is to provide a vibratory double-axially sensing micro-gyroscope, which includes a base, on center of which a supporting hub is arranged, and plural suspending arms are extended outwardly with equal altitude and in radial direction from the supporting hub and, at the outside end of the suspending arm, a platform is formed, and a capacitance sensing electrode or a static-electricity driving electrode is plated respectively at each side of the platform top, below which a static-electricity driving electrode or a capacitance sensing electrode is arranged; take a preferred embodiment of the present invention for example, if the capacitance sensing electrode is arranged at top of the platform and the static-electricity driving electrode is arranged below the platform, then the suspending arm and the platform will vibrate vertically by the attraction of the static-electricity when applying driving voltage, and the vibratory phase difference between two adjacent suspending arms and the platform is 180 degrees; when the gyroscope is rotated horizontally, the suspending arm and the platform will generate horizontal displacement caused by Coriolis force and, by measuring the change of capacitance value, the magnitude of the angular velocity of vibration is obtained; since its structure has symmetrical property, so it has sensing ability in both X or Y axes and, because it has superior stability and is able to resist environment noise and vibration, its sensing capability is enhanced and, since its machining method is simple, so it is adapted for mass production for having lower manufacturing cost.
Abstract:
A micromachined design and method with inherent disturbance-rejection capabilities is based on increasing the degrees-of-freedom (DOF) of the oscillatory system by the use of two independently oscillating proof masses. Utilizing dynamical amplification in the 4-degrees-of-freedom system, inherent disturbance rejection is achieved, providing reduced sensitivity to structural and thermal parameter fluctuations and damping changes over the operating time of the device. In the proposed system, the first mass is forced to oscillate in the drive direction, and the response of the second mass in the orthogonal direction is sensed. The response has two resonant peaks and a flat region between peaks. Operation is in the flat region, where the gain is insensitive to frequency fluctuations. An over 15 times increase in the bandwidth of the system is achieved due to the use of the proposed architecture. In addition, the gain in the operation region has low sensitivity to damping changes. Consequently, by utilizing the disturbance-rejection capability of the dynamical system, improved robustness is achieved, which can relax tight fabrication tolerances and packaging requirements and thus result in reducing production cost of micromachined methods.
Abstract:
The present invention discloses an isolated electrostatic biased resonator gyroscope. The gyroscope includes an isolated resonator having a first and a second differential vibration mode, a baseplate supporting the isolated resonator, a plurality of excitation affixed to the baseplate for exciting the first differential vibration mode, a plurality of sensing electrodes affixed to the baseplate for sensing movement of the gyroscope through the second differential vibration mode and a plurality of bias electrodes affixed to the baseplate for trimming isolation of the resonator and substantially minimizing frequency split between the first and second differential vibration modes. Typically, the isolated resonator comprises a proof mass and a counterbalancing plate with the bias electrodes disposed on the baseplate below.
Abstract:
A tuning fork vibrator includes a long plate-shaped vibration unit having a first principal surface and a second principal surface, a base disposed at one end of the second principal surface of the vibration unit in the longitudinal direction, and a slit for dividing the vibration unit into two legs defining a tuning fork along the longitudinal direction symmetrically in the width direction of the vibration unit. The slit is formed so as to include a portion of the base in the vicinity to the vibration unit.
Abstract:
A two-axis rate gyro has two articulation elements arranged sequentially. The first articulation element is connected with a drive shaft of the rate gyro and the second articulation element is connected with a gyro rotor. The two articulation elements are connected together by two narrow ribs located laterally with respect to a central bore and perpendicularly or radially with respect to the central axis of the articulation elements. Spring elements are provided in one of the articulation elements which act on pretensioned force-measuring elements and are tensioned with respect to one another. The spring elements deform elastically and symmetrically around the ribs under the influence of a sinusoidally alternating torque, so that the force-measuring elements are loaded and unloaded alternately and generate measurement signals proportional to the forces acting on them.
Abstract:
A gyroscope which comprises a gyroscopic element mounted to a base which is mounted coaxially to a spin motor. Preferably at least one hinge is between the gyroscopic element and the base. There is at least one piezoelectric crystal, preferably a bender element, having a base end, an outer end. A bender element provides an electrical signal as a function of bending. The base end of the crystal can be connected to the base and the crystal extends from the base with the crystal having a major plane transverse to the spin axis. The outer end of the crystal is connected to the gyroscopic element via a crystal restraint having a degree of freedom of movement parallel to the spin axis. Preferably, the crystal restraint is a wire connected on one end to the crystal and on the opposite end to the gyroscopic element. The restraint wire is preferably parallel to the spin axis.
Abstract:
A flight motion simulator includes a unit under test supported on a stationary frame for angular and translational movement along pitch, roll, and yaw axes. A rotor element is secured to the unit under test and has a spherical configuration. Magnetic bearings supported by the stationary frame support the rotor element in three degrees of freedom of movement. A drag-cup induction motor is mounted on the frame and connected to the unit under test to generate three degrees of freedom of movement by generating a rotating magnetic flux in a stator assembly to induce a corresponding flow of currents in the rotor element to produce torque and motion in the unit under test in the same direction as the flux movement in the stator assembly.