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公开(公告)号：US20150019129A1
公开(公告)日：2015-01-15
申请号：US14327679
申请日：2014-07-10
CPC分类号： G01C21/005 , G01C15/00 , G01C17/00 , G01C19/38 , G01C21/10 , G01S19/35 , G01S19/39 , G01S19/53 , G01S19/54
摘要： A device is described herein for determining azimuth comprising a MEMS inertial measurement unit (IMU), a GPS system comprising a GPS antenna and receiver, and a processor configured to receive data from said IMU and from said GPS system, said processor being configured to process said IMU data and said GPS data to derive a true north reference based on said IMU data and said GPS data. A method for determining azimuth is also described herein.
摘要翻译： 本文描述了用于确定包括MEMS惯性测量单元（IMU）的方位角的装置，包括GPS天线和接收器的GPS系统以及被配置为从所述IMU和所述GPS系统接收数据的处理器，所述处理器被配置为处理 所述IMU数据和所述GPS数据，以基于所述IMU数据和所述GPS数据导出真正的北参考。 本文还描述了一种用于确定方位角的方法。
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公开(公告)号：US20220120564A1
公开(公告)日：2022-04-21
申请号：US17402817
申请日：2021-08-16
IPC分类号： G01C19/5712 , G01C25/00
摘要： A vibrating structure gyroscope comprises a resonant structure arranged to vibrate under stimulation from a primary drive electrode. A drive system is arranged to vibrate the vibrating structure at a resonance frequency. An automatic gain control unit varies an amplitude of a primary drive signal (PD). A controller operates the gyroscope such that in a first mode of operation, the automatic gain control unit varies an amplitude of the drive signal (PD) between an operating range defined by upper and lower bounds and in a second mode operation, in which the automatic gain control unit sets the amplitude of the drive signal (PD) to a predetermined level outside of the operating range. In the second mode of operation an amplitude of a primary sense signal (PP) is measured after a predetermined time period to determine an oscillation cycle count during said predetermined time period.
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公开(公告)号：US20180340779A1
公开(公告)日：2018-11-29
申请号：US15964147
申请日：2018-04-27
摘要： An inertial measurement system comprising: a first, roll gyro with an axis oriented substantially parallel to the spin axis of the projectile; a second gyro and a third gyro with axes arranged with respect to the roll gyro; a controller, arranged to: compute a current projectile attitude from the outputs of the first, second and third gyros; operate a Kalman filter that receives a plurality of measurement inputs including at least roll angle, pitch angle and yaw angle and that outputs at least a roll angle error; initialise the Kalman filter with a roll angle error uncertainty representative of a substantially unknown roll angle; generate at least one pseudo-measurement from stored expected flight data; provide said pseudo-measurement(s) to the corresponding measurement input of the Kalman filter; and apply the roll angle error from the Kalman filter as a correction to the roll angle.
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公开(公告)号：US20210033399A1
公开(公告)日：2021-02-04
申请号：US16713427
申请日：2019-12-13
IPC分类号： G01C19/5776 , G01C19/5684 , H03D3/00
摘要： A method of demodulating a MEMS sensor pickoff signal from a vibrating resonator of said sensor, the method comprising: sampling the pickoff signal with an asynchronous ADC at a sampling rate of at least 50 times the resonant frequency of the resonator to generate a stream of samples; generating a first value by combining samples from said stream of samples according to a selected operation, said operation being selected in dependence on a synchronous clock signal that is synchronous to the resonant frequency of the resonator, said synchronous clock signal having a frequency at least twice the resonant frequency of the resonator; and counting the number of samples contributing to the first value. The increased sampling rate of the pickoff signal allows a much higher number of samples to be taken into account, thereby reducing noise. However, the ADC asynchronously from the resonator of the MEMS sensor.
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公开(公告)号：US20170363428A1
公开(公告)日：2017-12-21
申请号：US15604745
申请日：2017-05-25
摘要： An inertial measurement system for a spinning projectile comprising: first (roll), second and third gyros with axes arranged such that they define a three dimensional coordinate system; at least a first linear accelerometer; a controller, arranged to: compute a current projectile attitude comprising a roll angle, a pitch angle and a yaw angle; compute a current velocity vector from the accelerometer; combine a magnitude of said velocity vector with an expected direction for said vector to form a pseudo-velocity vector; provide the velocity vector and the pseudo-velocity vector to a Kalman filter that outputs a roll gyro scale factor error calculated as a function of the difference between the velocity vector and the pseudo-velocity vector; and apply the roll gyro scale factor error from the Kalman filter as a correction to the output of the roll gyro.
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