IMU/VRU/AHRS

ER-AHRS-10 (6 deg/hr)
1.Industrial-grade inertial sensors
2.3 ° dynamic attitude accuracy
3.Stable heading output
4.Factory calibrated in full temperaturerange

IMU/VRU/AHRS

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    Introduction

    ER-AHRS-10 IMU/VRU/AHRS

    Introduction
    The ER-AHRS-10 inertial sensing system integrates industrial-grade MEMS gyroscope and accelerometer, which can output 3D angular velocity, acceleration, magnetic field information, and fused 3D azimuth angles.When connected to a satellite navigation (GNSS) signal, fused position and velocity information can be output. ER-AHRS-10 includes ER-AHRS-10U Inertial Measurement Unit (IMU), ER-AHRS-10V Vertical Reference System (VRU), ER-AHRS-10A Attitude Reference System (AHRS)

    The ER-AHRS-10 is embedded with  multi-sensor fusion algorithm, which has been calibrated at the factory in all temperature ranges to ensure the excellent performance of the system in harsh environments. The compact design of the ER-AHRS-10 makes it easy for customers to integrate applications and shorten the development cycle.

    The ER-AHRS-10 has a dynamic attitude detection accuracy of 0.3° and provides a stable, low-drift relative heading output and a drift-free absolute heading output. It can meet the attitude, direction stability control, positioning and navigation needs of various carriers in complex and harsh application environments.

    Features
    Stable heading output
    3 ° dynamic attitude accuracy
    Industrial-grade inertial sensors
    Gyro bias instability: 6 °/h
    Accelerometer bias instability: 0.05mg

    Application
    Robots, unmanned vehicles
    Construction machinery, intelligent agricultural machinery
    Satcom on the move/Communication in Moving

    Product model information

    Items ER-AHRS-10U ER-AHRS-10V ER-AHRS-10A
    Angular velocity, acceleration
    Attitude angle
    Relative heading angle
    Absolute heading angle

    Specifications:

    Attitude orientation performance

    Attitude angle 0.3 ° 1σ RMS
    Heading angle Relative heading angle*

    Absolute heading angle**

    0.8 ° 1σ RMS
    1 ° 1σ RMS
    Sensor parameters
    Gyroscope Accelerometer Magnetic sensors
    Range                                    ±500 °/s ±16g ±8 Gauss
    Non-linearity                          ±0.05%FS ±0.5%FS ±0.2%FS
    Bias instability***                    6 °/h 0.05mg -
    Noise density                         0.015 °/s/√ Hz 100μg/√ Hz 0.4mG (RMS)
    Bandwidth                              116Hz 116Hz -
    System parameters
    Input voltage                                3.3- 16VDC Size 37.7*24*9.5mm
    Power consumption                     250mW Weight 15.5g
    Operating temperature                 -40~85℃ Hardware interface SPI UART
    Output frequency 200Hz
    Note: The above parameters are typical values

    * Provides a relative heading angle without reference,Regular motion drift<0.8 °/min,Static drift<0.8 °/hr。

    ** In a homogeneous magnetic field environment

    *** Allan variance,1σ @25℃


    Application Techniques

    1.IMU and GPS fusion algorithm principle

    2.MEMS IMU error analysis and compensation

    3.Reusable spacecraft IMU dynamic accuracy assessment method

    4.Research on MEMS IMU error modeling and temperature compensation technology

    5.Calibration method and error analysis of low-precision MEMS IMU

    6.MEMS-IMU error calibration compensation method that does not rely on precision turntable


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