Abstract: The invention relates to a weight and reference quaternion correction unscented quaternion estimation method, comprising: obtaining measurement data as quantity measurement through a gyro and a star sensor; establishing a quaternion-based discrete spacecraft nonlinear state space model; estimating an error quaternion, a gyro drift and a corresponding error covariance at a k moment by using an unscented quaternion estimator based on parameter and reference quaternion correction at a k?1 moment; and setting a filtering time as Ntime, if k<Ntime, then repeating the step 3, if k=Ntime, then finishing filtering, and outputting the attitude quaternion, the gyro drift and the corresponding error covariance.

Abstract: A system and method for predicting aircraft nonlinear instability includes the steps of: (1) a pre-built aircraft state parameters for all possible flight conditions, (2) real time measuring flight parameters to determine aircraft state, (3) calculating the inertial coupling frequencies and periods as well as the nonlinear instability threshold based on the nonlinear instability theory recently developed by the inventor, (4) providing a first warning signal if the threshold is approached, (5) providing a second warning signal if the threshold has been exceeded.

Abstract: A vibrating element includes a base part, drive arms containing first surfaces and second surfaces having front-back relations with the first surfaces, having groove portions provided on the first surface sides, and extended from the base part in extension directions, and drive parts provided to contain piezoelectric layers on the second surfaces, and section shapes of the drive arms orthogonal to the extension directions contain asymmetric section shapes with respect to virtual center lines passing through centers of widths in directions orthogonal to the extension directions.

Abstract: A microelectromechanical device includes: a body; a movable mass, elastically coupled to the body and oscillatable with respect to the body according to a degree of freedom; a frequency detector, configured to detect a current oscillation frequency of the movable mass; and a forcing stage, capacitively coupled to the movable mass and configured to provide energy to the movable mass through forcing signals having a forcing frequency equal to the current oscillation frequency detected by the frequency detector, at least in a first transient operating condition.

Abstract: The invention relates to a controller, and more particularly, to systems, devices and methods of controlling a sensor having a resonating mass. The controller includes: an analog-to-digital converter (ADC) unit for extracting a digitized sensor signal from the sensor signal; a phase controller for generating, based on the digitized sensor signal, a phase-controlled signal that is locked in phase with the digitized sensor signal; an amplitude controller for applying a gain to the digitized sensor signal to thereby generate an amplitude-adjusted signal; a modulator for modulating the amplitude-adjusted signal to thereby generate a modulated signal; and a phase shifter for shifting the phase of the modulated signal by 90 degrees. The output signal from the phase shifter is amplified and input to the drive for exciting the resonating mass, to thereby form a closed resonance loop for controlling the oscillation amplitude of the resonating mass.

Abstract: A temperature sensor package includes a temperature sensor having a first side and a second side, wherein the first side of the temperature sensor includes an active region configured for coupling with a target area for temperature measurement of an object. The temperature sensor package further includes a circuit board having a first side and a second side, the first side of the circuit board coupled to the second side of the temperature sensor, wherein the circuit board provides thermal insulation between the active region of the temperature sensor and an environment on the second side of the circuit board.

Abstract: A disk resonator gyroscope includes a quartz base, a quartz resonator disk having a central pillar connected to the base, the quartz resonator disk having a surface facing the base and having plurality of circumferential slots in the surface of the quartz resonator disk around the central pillar, and an electrode comprised of quartz and connected to the base outside of an outer edge of the resonator disk.

Abstract: A signal processing module (50) comprises a difference signal generating module (60) for generating at least one difference signal (?) from a first and a second acceleration measurement vector signal (S1, S2), the first and the second acceleration measurement vector signal (S1, S2) respectively comprising a first and a second sequence of vector signal samples, the vector signal samples comprising at least a first and a second linearly independent acceleration measurement signal component, wherein the vector signal samples represent a measurement result of an acceleration sensor having a variable orientation as a function of time, wherein samples in the first sequence have a corresponding sample in the second sequence.

Abstract: An on-chip navigation system, optionally combined with GPS (Global Positioning System) and/or an imaging array, which incorporates MEMS (MicroElectroMechanical Systems) components is possible by the use of careful material selection and novel bonding techniques used during fabrication. The use of MEMS components permits many of the components of a typical inertial navigation system to reside on a single chip. Because the components are in close proximity, the components can then be used to monitor the environmental changes of the chip, such as temperature and vibration, and correct for the resulting offsets of other components. This allows improved system performance even if the individual sensor components are not ideal.

Abstract: A method is disclosed for detecting the correct rotational direction of a centrifugal apparatus. The method can include detecting the correct rotational direction of the centrifugal apparatus based on an acceleration test and/or a deceleration test. The detecting of correct rotational direction of the centrifugal apparatus can include comparing an acceleration time (t1,acc) for a first direction with an acceleration time (t2,acc) for a second direction, whereby shorter acceleration time can be interpreted as an indication of correct rotational direction; and/or comparing a deceleration time (t1,dec) of the first direction with a deceleration time (t2,dec) of the second direction, whereby longer deceleration time can be interpreted as an indication of correct rotational direction.

Abstract: An innovative configuration of Miniaturized Smart Self-calibration EPD for mortar applications, as the azimuth/heading and elevation measurement device. This innovative EPD configuration uses only two FOGs or DTG and accelerometers and it is self-contained. This leads to a new EPD implementation that produces a small and light device with lower cost and adequate accuracy for the small dismounted mortar applications.

Abstract: Gyroscopes using surface electrodes are provided. In this regard, a representative microelectromechanical systems (MEMS) gyroscope, among others, includes a top substrate and a bottom substrate. The top substrate includes an outermost structure that is open and enclosed and a first driving structure that is disposed within the outermost structure and includes first driving electrodes disposed on a bottom surface. The bottom substrate is disposed below the top substrate and includes second driving electrodes disposed on a top surface of the bottom substrate. The second driving electrodes are substantially aligned below the first driving electrodes such that a force can be applied to the first driving structure by an electrostatic force generated between the first and second driving electrodes. The first and second driving electrodes are also configured to provide a capacitance signal based on the movement of the first driving structure.

Abstract: An on-chip navigation system, optionally combined with GPS (Global Positioning System) and/or an imaging array, which incorporates MEMS (MicroElectroMechanical Systems) components is possible by the use of careful material selection and novel bonding techniques used during fabrication. The use of MEMS components permits many of the components of a typical inertial navigation system to reside on a single chip. Because the components are in close proximity, the components can then be used to monitor the environmental changes of the chip, such as temperature and vibration, and correct for the resulting offsets of other components. This allows improved system performance even if the individual sensor components are not ideal.

Abstract: The effects of IMU gyro and accelerometer bias errors are significantly reduced in accordance with the present teachings by a system or method for commanding an IMU or vehicle through a series of preprogrammed maneuvers. The maneuvers can be designed to minimize the effects of other gyro errors including scale factor errors, nonlinearities, cross coupling/misalignment, and scale factor asymmetries. A sample maneuver is provided which demonstrates performance based on a sequence of roll and yaw maneuvers resulting in zero build up of error at the end of a maneuver cycle period as a result of these errors. Modification of the system involves the addition of control logic to determine the maneuver period, maneuver rate, and vehicle orientation. No additional hardware beyond possible fuel required to perform the maneuver is required.

Abstract: The system includes a mobile vessel having a body axis and a steering mechanism. A three-axis gyroscope is mounted within the vessel. A three-axis magnetometer is mounted within the vessel. A programmable device communicates with the three-axis gyroscope, the three-axis magnetometer, and the steering mechanism. The three-axis gyroscope may include three single axis gyroscopes.

Abstract: A measuring device 1 for measuring structures is provided, wherein the measuring device including two inertial measuring units 3, 4 arranged at a distance from each other. The measuring device can be provided with means for engaging the constructions that are measured. Also, an arrangement including a measuring device and a base station 21 providing a reference point for the measuring device is provided. Moreover, a kit including the measuring device and adaptors are provided, wherein the adaptors can provide an interface between the measuring device and a measured construction. A method for measuring a stationary construction is also provided, using a measuring device, preferably a measuring kit.

Abstract: A system and method for more accurately and robustly estimating navigation state of a vehicle by adaptively processing signals from an inertial sensor assembly and other sensors. A navigation system receives signals from two or more sensors to evaluate and correct the attitude estimated by an Extended Kalman Filter (EKF). The navigation system selects sensor signals from the other sensor assemblies and processes the selected sensor signals in conjunction with estimates from the inertial navigation module to obtain more accurate estimates of the attitude. The parameters and conditions for using certain sensor signals may be adjusted based on the characteristics and configuration of the vehicle.

Abstract: A method and system for Self-calibrated Azimuth and Attitude Accuracy Enhancing are disclosed, wherein SAAAEMS approach is based on fully auto-calibration self-contained INS principles, not depending on magnetometers for azimuth/heading determination, and thus the system outputs and performance are not affected by the environmental magnetic fields. In order to reduce the system size and cost, this new innovative methods and algorithms are used for SAAAEMS system configuration and integration. Compared to a conventional INS for gyrocompassing, AGNC's approach uses a smaller number of high accuracy sensors: SAAAEMS uses only one 2-axis high accuracy gyro (for example, one DTG) instead of 3-axis; the third axis gyro is a MEMS gyro. It uses only 2 high accuracy accelerometers instead of 3, since the two accelerometers are used only for gyrocompassing not for navigation. These two changes to the conventional INS system configuration remarkably reduce the whole system size and cost.

Abstract: The present invention relates to a multiaxial gyroscope, which comprises a vibration-sensing device, a plurality of elastic connecting parts, a first substrate, and a plurality of electrodes. The first ends of the elastic connecting parts are adapted on the periphery of the vibration-sensing device. The sidewall of the first substrate connects with the second ends of the elastic connecting parts. The plurality of electrodes is located on the periphery of the vibration-sensing device and is opposite to the plurality of elastic connecting parts. The vibration-sensing device comprises a ring and a plurality of vibration blocks. By means of the vibration blocks, the sensing area as well as the driving amplitude of the gyroscope can be increased effectively. Thereby, the intensity of the sensed signals of the gyroscope can be enhanced.

Abstract: A micro-electro-mechanical sensor includes a microstructure having a mass which is movable with respect to a rest position, according to a predetermined degree of freedom, and a displacement-detecting device for detecting a displacement of the mass according to the predetermined degree of freedom. The displacement-detecting device includes a force feedback loop of a purely analog type, which supplies electrostatic forces tending to restore the mass to the rest position in response to a displacement of the mass according to the predetermined degree of freedom.

Abstract: The electrostatically-driven/capacitance-detection type gyro sensor has a sensing element including a movable part, the sensitivity of the sensing element and accordingly the sensitivity of a sensor output signal thereof being kept unchanged by controlling the amplitude of displacement or displacing velocity of the movable part and by using a reference voltage independent of variation of a power supply voltage, even there occurs a change in the vibrating state of the movable part due to temperature change or secular variation.

Abstract: A micro-electro-mechanical sensor includes a microstructure having a mass which is movable with respect to a rest position, according to a predetermined degree of freedom, and a displacement-detecting device for detecting a displacement of the mass according to the predetermined degree of freedom. The displacement-detecting device includes a force feedback loop of a purely analog type, which supplies electrostatic forces tending to restore the mass to the rest position in response to a displacement of the mass according to the predetermined degree of freedom.

Abstract: Method for fabricating a gyroscope including: fabricating a SMS wafer where a first wafer, a metal film, and a second wafer are sequentially stacked; forming a cantilever or a bridge shaped-structure on the relevant portion of the first wafer through the photolithography process; attaching to the surface of the first wafer, a first cap made of glass and having a predetermined space for sealing the movable structure in a vacuum state; separating and removing the metal film and the second wafer from the first wafer; and attaching to the backside of the first wafer, the second cap which is structurally and materially symmetric to the first cap. The SMS wafer is fabricated by depositing the metal film on the second wafer and bonding the first wafer on the metal film using metal paste or material of polymer series. With lower material costs, improvements in performance and characteristics can be achieved.

Abstract: A method for extracting components from signals in an electronic sensor (50) having a sensing element (52). The sensing element (52) generates a first signal (60) and a second signal (62). The method comprises the steps of: receiving the first signal (60) from the sensing element (52), the first signal (60) having a frequency at an event; sampling the second signal (62) from the sensing element (52) based on the frequency of the event, the second signal (62) having a plurality of components, one of the plurality of components being a first component of interest (112, 114); generating a synchronized second signal (100) in a time domain, the second signal (62) having the plurality of components; generating complex data (110) in a frequency domain from the synchronized second signal (100) in the time domain; determining the first component of interest (112, 114) from the complex data (110); and normalizing the first component of interest (112, 114) using amplitude information from the first signal (60).

Abstract: An apparatus for determining an instrument boresight azimuth heading. A typical apparatus comprises a gyro having a first input and a first output and a rocking angle generator having a second output, wherein the second output is communicatively coupled to the first input of the gyro, producing a demodulated signal at the first output. A signal multiplier is communicatively coupled to the second output and the demodulated signal for multiplying the second output and the demodulated signal and producing a multiplied signal and a filter communicatively coupled to the multiplied signal for producing a filtered output.

Abstract: A method for extracting components from signals in an electronic sensor (50) having a sensing element (52). The sensing element (52) generates a first signal (60) and a second signal (62). The method comprises the steps of: receiving the first signal (60) from the sensing element (52), the first signal (60) having a frequency at an event; sampling the second signal (62) from the sensing element (52) based on the frequency of the event, the second signal (62) having a plurality of components, one of the plurality of components being a first component of interest (112, 114); generating a synchronized second signal (100) in a time domain, the second signal (62) having the plurality of components; generating complex data (110) in a frequency domain from the synchronized second signal (100) in the time domain; and determining the first component of interest (112, 114) from the complex data (110). There is also a system in an electronic sensor (50) according to the above-described methods.

Abstract: The object of the present invention is to improve the sensitivity of a vibrator having at least one bending vibration arm vibrating along a specified plane in bending mode, and a base portion provided at one end of the arm. A vibrator 20A has at least one bending vibration arms 14, 15 vibrating along a specified plane in bending mode, base portions 1 and 22 provided at one ends of the arms 14 and 15, respectively, and weight portions 9, 12 provided at the other ends of the arms 14 and 15, respectively. Grooves 5 and 6 are formed on one main face 33 and the other main face 34 substantially parallel with the specified plane of the bending vibration arms 14 and 15, respectively.

Abstract: A vehicle is provided, including a vehicle body; at least one vehicle element pivotally mounted to the vehicle, the vehicle element configured to pivot through an angle not more than 360 degrees; and a measuring arrangement configured to measure an angular velocity of the at least one vehicle element.

Abstract: A hybrid stabilization system for isolating a pointing vector of a gimbal from the motion of a vehicle base is provided. The hybrid stabilization control system includes a rate feedback loop generating a rate feedback compensation value in response to a measured rate difference between a pointing vector rate of motion and a vehicle base rate of motion, a rate feedforward loop generating a rate feedforward compensation value in response to a measured inertial vehicle base rate of motion, a position feedback loop generating a position feedback compensation value in response to a measured position difference between a pointing vector angular position and a vehicle base angular position, a position feedforward loop generating a position feedforward compensation value in response to a measured inertial vehicle base angular position.

Abstract: A vibrating structure gyroscope comprises a resonant body, drive transducer means for driving resonant motion of the body, pick-off means for producing signals representative of the resonant motion, and signal processing means for extracting z-axis orientation information and x- and y-axis rate information from the signals. The resonant body is planar and the resonant motion takes place in a vibration mode pattern whose orientation angle with respect to the body varies in accordance with z-axis orientation of the body and couples energy into an out-of-plane response mode motion in accordance with rotation of the body about the x- or y-axis. Signal processing means resolves the out-of-plane response mode motion with reference to a z-axis orientation signal to extract the x- and y-axis rate information.

Abstract: A self contained sensor apparatus generates a signal that corresponds to at least two of the three orientational aspects of yaw, pitch and roll of a human-scale body, relative to an external reference frame. A sensor generates first sensor signals that correspond to rotational accelerations or rates of the body about certain body axes. The sensor may be mounted to the body. Coupled to the sensor is a signal processor for generating orientation signals relative to the external reference frame that correspond to the angular rate or acceleration signals. The first sensor signals are impervious to interference from electromagnetic, acoustic, optical and mechanical sources. The sensors may be rate sensors. An integrator may integrate the rate signal over time. A drift compensator is coupled to the rate sensors and the integrator. The drift compensator may include a gravitational tilt sensor or a magnetic field sensor or both.