Honeywell International Inc.

Other

Timothy J Hanson

Mark W Weber

Drew A Karnick

Owen D Grossman

Keith F Winegar

Max C Glenn

Jens M Henrickson

David S Willits

Jason Daniel Graham

Terrance Troske

Matthew Schlager

Saul LaCoursiere

Todd L Loren Braman

Saul Lacoursiere

A method and system for providing gyroscope bias self-calibration are described herein. The method comprises powering on one or more gyroscopes; after a predetermined first period of time, and upon determining that the one or more gyroscopes is stationary, measuring input rates of rotation during a predetermined second period of time; and determining an average rate of rotation for each gyroscope channel based upon the measured input rates of rotation during the predetermined second period of time. After determining the average rate of rotation and after the predetermined second period of time, the method further comprises commencing additional measurements by the one or more gyroscopes; determining calibrated gyroscope measurements by subtracting the average rate of rotation from each of the additional measurements; and providing, at the output of the one or more gyroscopes, the calibrated gyroscope measurements.

Methods for approximate inertial sensor bias self-calibration

A method for generating a sensor output from the outputs of first and second sensors is provided. The method comprising receiving the outputs from the first and second sensors; estimating an offset between the outputs of the first and second sensors over a first range of outputs; adjusting the output of the second sensor based on the estimated offset; and generating a sensor output, based on the output of the first sensor, the adjusted output of the second sensor and a blending function that blends the output of the first sensor and the adjusted output of the second sensor.

Sensor blending with offset adjustment

A hybrid inertial measurement unit (IMU) comprises: a low frequency (LF) sensor providing a first signal containing information for a first parameter of the hybrid IMU; a shock resistant (SR) sensor providing a second signal containing information for the first parameter, wherein the SR sensor is resistant to destabilization during a destabilizing operational period; and a processor, wherein the processor further comprises: a weighting factor computation module to compute a weight to be applied to the first signal and to compute a weight to be applied to the second signal; a LF weighting module to apply the computed weight to the first signal to create a weighted first signal; a SR weighting module to apply the computed weight to the second signal to create a weighted second signal; and a compensator to combine the weighted first signal and the weighted second signal to create a compensated signal containing information for the first parameter.

Hybrid inertial measurement unit

One embodiment is directed towards an inertial measurement unit (IMU) for measuring an input rate of rotation about an input axis. The IMU includes a first three dimensional gyroscope disposed such that a first axis of its three axes is oriented at a skew angle in degrees away from a reference plane, wherein the reference plane is normal to the input axis. The IMU also includes one or more processing devices coupled to the first gyroscope. The IMU also includes one or more data storage devices coupled to the one or more processing devices, the one or more data storage devices including instructions which, when executed by the one or more processing devices, cause the one or more processing devices to calculate the input rate of rotation based on dividing a sensed rate of rotation about the first axis by the sine of the skew angle.

High rate rotation sensing

A method of controlling exposed glass charging in a micro-electro-mechanical systems (MEMS) device is disclosed. The method includes providing a MEMS device comprising a proof mass positioned apart from at least one sense plate and at least one outboard metallization layer, wherein at least one conductive glass layer is coupled to the sense plate and the outboard metallization layer, the conductive glass layer including at least one exposed glass portion near the proof mass; and applying a first voltage to the sense plate and a second voltage to the outboard metallization layer. The first voltage is separated from the second voltage by a predetermined voltage level such that the exposed glass portion has an average voltage corresponding to a voltage midway between the first voltage and the second voltage.

Reducing the effect of glass charging in MEMS devices

Systems and methods for isolated sensor device protection are provided. In one embodiment, an isolated sensor device comprises: a housing having an isolation chamber; an isolator sealed within the isolation chamber; an inertial sensor assembly sealed within the isolation chamber, the inertial sensor assembly coupled to an inner surface of the isolation chamber by the isolator; and at least one progressive impact interface applied to a periphery of the inertial sensor assembly, wherein the at least one progressive impact interface extends outward from the inertial sensor assembly towards the inner surface.

Systems and methods for isolated sensor device protection

A micro-electro-mechanical systems (MEMS) device comprises at least one proof mass configured to have a first voltage and a motor motion in a first horizontal direction. At least one sense plate is separated from the proof mass by a sense gap, with the sense plate having an inner surface facing the proof mass and a second voltage different than the first voltage. A set of stop structures are on the inner surface of the sense plate and are electrically isolated from the sense plate. The stop structures are configured to prevent contact of the inner surface of the sense plate with the proof mass in a vertical direction. The stop structures have substantially the same voltage as that of the proof mass, and are dimensioned to minimize energy exchange upon contact with the proof mass during a shock or acceleration event.

MEMS device mechanism enhancement for robust operation through severe shock and acceleration

Putter head

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.

Gyroscope dynamic motor amplitude compensation for enhanced rate estimation during startup

A golf putter includes a putter head, a shaft and hand grip. The putter head includes a lower curved striking face and a substantially straight upper striking face. The straight striking face extends upward vertically from an upper end of the curved striking face. A height as measured from a bottom surface to a junction of the straight striking face and the curved striking face is at least one half the outer diameter of a regulation golf ball. An alignment striking line is created on a top and middle of the putter head. The hand grip is attached to one end of the shaft. The other end of the shaft is inserted into a top of the putter head. An impact plate is attached to a bottom and front of the putter head. A plurality of horizontal grooves are formed in the impact plate.

Golf putter

A method of estimating bias errors for an air vehicle in flight under high spin conditions is provided. The method comprises collecting a first set of data samples at a first time and collecting a second set of data samples at a second time. The first time and the second time occur after deployment of the air vehicle and before canard shock. The first and second sets of data samples comprise roll rate data from at least a first gyroscope and acceleration data from at least a first accelerometer. At least a first estimated accelerometer bias from the first and second sets of data samples is calculated.

Real-time compensation of inertial sensor bias errors under high spin rate conditions

A sensor system and method for determining a relative direction to true north is provided. The system comprises at least one angular rate sensor, such as a MEMS sensor, which has an input axis and a rotation axis. The sensor comprises a motor drive structure, a motor signal output from the motor drive structure, a gyroscope, and a sensor rate output from the gyroscope for a sensor rate signal. A frequency divider is in operative communication with the motor signal output, and a spinning device is coupled to the angular rate sensor. A spinning device motor is coupled to the spinning device and is in operative communication with the frequency divider. The spinning device motor has an axis of rotation that is substantially perpendicular to the input axis of the sensor. The spinning device motor is configured to be driven by a periodic signal from the sensor. A position of the spinning device is synchronized to the periodic signal to generate a spinning device position signal. A phase detector is in operative communication with the spinning device motor and with the sensor rate output. The relative direction to true north is determined from a phase differential between the spinning device position signal and the sensor rate signal.

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Plymouth, MN, United States of America

Timothy J Hanson