Compact, Flat-Quartz, Vibratory, Angular-Rate Sensor Module Using T-Shaped Resonators

2002 ◽  
Author(s):  
S. Ishikawa ◽  
T. Kikuchi ◽  
T. Soma ◽  
Y. Ohsugi ◽  
M. Tani ◽  
...  
Keyword(s):  
Angular Rate ◽  
Angular Rate Sensor ◽  
Sensor Module ◽  
Rate Sensor

Head acceleration measurement techniques: Reliability of angular rate sensor data in helmeted impact testing

2017 ◽  
Vol 232 (2) ◽  
pp. 176-181 ◽  
Author(s):  
Bryan R Cobb ◽  
Abigail M Tyson ◽  
Steven Rowson
Keyword(s):  
Root Mean Square ◽  
Angular Rate ◽  
Angular Acceleration ◽  
Impact Testing ◽  
Sensor Data ◽  
Mean Square ◽  
Head Acceleration ◽  
Angular Rate Sensor ◽  
Impact Tests ◽  
Rate Sensor

This study sought to evaluate the suitability of angular rate sensors for quantifying angular acceleration in helmeted headform impacts. A helmeted Hybrid III headform, instrumented with a 3-2-2-2 nine accelerometer array and angular rate sensors, was impacted (n = 90) at six locations and three velocities (3.1, 4.9, and 6.4 m/s). Data were low-pass filtered using Butterworth four-pole phaseless digital filters which conform to the specifications described in the Society of Automotive Engineers J211 standard on instrumentation for impact tests. Nine accelerometer array data were filtered using channel frequency class 180, which corresponds to a −3 db cutoff frequency of 300 Hz. Angular rate sensor data were filtered using channel frequency class values ranging from 5 to 1000 Hz in increments of 5 Hz, which correspond to −3 db cutoff frequencies of 8 to 1650 Hz. Root-mean-square differences in peak angular acceleration between the two instrumentation schemes were assessed for each channel frequency class value. Filtering angular rate sensor data with channel frequency class values between 120 and 205 all produced mean differences within ±5%. The minimum root-mean-square difference of 297 rad/s2 was found when the angular rate sensor data were filtered using channel frequency class 175. This filter specification resulted in a mean difference of 28 ± 297 rad/s2 (1.8% ± 8.6%). Condition-specific differences (α=0.05) were observed for 11 of 18 test conditions. A total of 4 of those 11 conditions were within ±5%, and 10 were within ±10%. Furthermore, the nine accelerometer array and angular rate sensor methods demonstrated similar levels of repeatability. These data suggest that angular rate sensor may be an appropriate alternative to the nine accelerometer array for measuring angular head acceleration in helmeted head impact tests with impactor velocities of 3.1–6.4 m/s and impact durations of approximately 10 ms.

Sine-Wave Exciting Circuit for Quartz Vibrating Gyroscope

2013 ◽  
Vol 562-565 ◽  
pp. 417-420
Author(s):  
Qing Yi Wang ◽  
Xiao Wei Liu ◽  
Rui Zhang ◽  
Liang Yin ◽  
Zhi Ping Zhou
Keyword(s):  
High Performance ◽  
Small Volume ◽  
Angular Rate ◽  
Sine Wave ◽  
Processing Technology ◽  
Angular Rate Sensor ◽  
Square Wave ◽  
Rate Sensor ◽  
Is Design ◽  
Cmos Processing

Quartz vibrating gyroscope is a kind of angular rate sensor which is the compromise between the high performance and the small volume. Improvement of the performance is a focus of reach. In this paper, a sine-wave exciting method is discussed. A sine-wave exciting circuit is design and processed with 0.5μm CMOS processing technology. During comparing the sine-wave exciting response and the square-wave one, the sine-wave exciting circuit is more beneficial to improve the performance of the quartz vibrating gyroscope.

scholarly journals Design and Implementation of a Digital Angular Rate Sensor

Sensors ◽  
2010 ◽  
Vol 10 (11) ◽  
pp. 9581-9589 ◽  
Author(s):  
Li-Feng Wu ◽  
Zhen Peng ◽  
Fu-Xue Zhang
Keyword(s):  
Angular Rate ◽  
Angular Rate Sensor ◽  
Design And Implementation ◽  
Rate Sensor

Active Roll Control of Heavy Single Unit Vehicles Employing MEMS Angular Rate Sensors

2007 ◽  
Author(s):  
Samuel F. Asokanthan ◽  
Ye Tian ◽  
Tianfu Wang
Keyword(s):  
Single Unit ◽  
Dynamic Models ◽  
Low Cost ◽  
Angular Rate ◽  
Micro Electro Mechanical System ◽  
Angular Rate Sensor ◽  
Linear Quadratic ◽  
Roll Control ◽  
Active Roll Control ◽  
Rate Sensor

The present paper is concerned with the use of active roll control to improve the roll stability of heavy road-vehicles and the application of Micro-electro-mechanical System (MEMS) angular rate sensors in the feedback monitoring. For this purpose, mathematical models that represent the roll/yaw dynamics for a torsionally rigid Single Unit Vehicle (SUV) is presented. The state-space models that represent the vehicle dynamics are also developed for the purpose of performing numerical simulations. A linear Quadratic Gaussian (LQG) based controller, using Kalman estimator to estimate certain states, is employed to design a full-state active roll control system. A mathematical model that represents the dynamic behavior of a low-cost MEMS gyroscope is derived for the purpose of investigating the suitability of applying this class of angular rate sensor in the roll control of heavy vehicles. Some reliability issues related to MEMS sensors, such as noise and drift, are introduced and included in vehicle dynamic models.

Angular Rate Sensor Based on a Solid-State Wave Gyroscope with a Metal Resonator for Attitude Control, Stabilization and Navigation Systems

2021 ◽  
Vol 22 (7) ◽  
pp. 374-382
Author(s):  
V. Ya. Raspopov ◽  
V. V. Likhosherst
Keyword(s):  
Attitude Control ◽  
Angular Rate ◽  
Operating Conditions ◽  
Simultaneous Action ◽  
Navigation Systems ◽  
Angular Rate Sensor ◽  
Manufacturing Defects ◽  
Vibration Localization ◽  
Resonance Frequencies ◽  
Rate Sensor

The article describes the methods and test results of a solid-wave gyroscope (SVG) — an angular rate sensor (ARS), developed at the Department of Control Devices, Tula State University and manufactured by the serial plant of JSC "Michurinsky Plant" Progress "according to the technology it worked out. The metal resonator SVG-ARS is made of an elinvar alloy and has a cylindrical structure of different thickness, the lower part of which, with a smaller wall thickness, acts as a suspension for the upper cylinder, the resonator itself, which has a conical shape, providing better vibration localization at its end edge. Technological manufacturing defects, different frequencies and variability, are eliminated by balancing " by mass" based on the removal of excess metal at certain points on the end edge of the resonator. The electronic module provides the second mode of primary and secondary oscillations of the resonator edge arising during rotation and creates a signal to compensate for the Coriolis and quadrature components of the output signal at the nodes. The maximum amplitudes of the excitation and compensation signals do not exceed 10 V. Therefore, at large values of mechanical influences, the compensation circuit may not work out the increased signal and the SVG-ARS loses its operability. The total processing time of the compensation signal does not exceed 1 μs. The maximum power consumption of the electronic module is not more than 4 W. When testing for mechanical and temperature effects, the norms were used that are typical for similar devices (angular rate sensors) used on board aircraft. The tests were carried out on the bench equipment of a specialized enterprise. The stability of the zero signal and the scale factor was determined under the simultaneous action of the measured speed and temperature on the SVG-ARS. The values of the random walk and the instability of the zero signal were obtained from the Allan deviation plots. Their values provide a basis for the conclusion about the possibility of using the developed SVG for several hours on board dynamic aircraft in orientation, stabilization and navigation systems. It was found that SVG-ARS possesses impact strength and restores its measuring ability after impact. Tests for vibration resistance revealed resonance frequencies and frequency rangesin which the tested VTG-DUS sample can be used without significant modification. The results of vibration tests can be used to refine the design and control electronics for the operating conditions of a particular aircraft.

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