Er Mimu 04

Low-Cost Attitude-Control MEMS IMU

ER-MIMU-04 (1 deg/hr)
1. Gyro bias instability: 1 deg/hr;
2. Low cost and small size;
3. 3 axis gyroscope & 3-axis accelerometer

Low-Cost Attitude-Control MEMS IMU

Er Mimu 04

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    Introduction

    Low-cost-Attitude-control-MEMS-IMU for AttitudeLow-cost Attitude-control MEMS IMU for tall buildingLow-cost Attitude-control MEMS IMU for mining

    Low-Cost Attitude-control MEMS IMU 

    Introduction
    Inertial Measurement Unit, referred to as IMU, is a device to measure the attitude angle (or angular velocity) and acceleration of the three axis of the object. Gyroscope and accelerometer are the core devices of inertial navigation system (INS). With the built-in accelerometer sensor and gyroscope, the IMU can measure the linear acceleration and rotation angular velocity from three directions and can obtain the attitude, velocity and displacement information of the carrier through the resolving.
    ER-MIMU-04 uses MEMS accelerometer and gyroscope with high quality and reliability, RS422 and external communication, baud rate can be flexibly set between 230400~921600, through the communication protocol to set the user’s required communication baud rate. With X, Y, Z three-axis precision gyro, X, Y, Z three-axis accelerometer with high resolution, can be output by RS422 X, Y, Z three axis of gyroscope and accelerometer’s original hexadecimal complement data (including gyro hexadecimal complement the numerical temperature, angle, the accelerometer hexadecimal temperature, the acceleration hexadecimal complement number); It can also output float dimensionless values of the gyroscope and accelerometer processed by the underlying calculation.

    Application 
    Azimuth, attitude, position measuring and keeping In GNSS-assisted INS
    Heading, pitch, roll measuring In AHRS for UAV
    Motion survey and keeping in MRU
    Attitude & azimuth keeping, positioning in IMU
    Guidance, navigation, control in tactical MEMS weapon system
    Stabilizing & Pointing in satellite antenna,target tracking system
    Robotic Control & Orientation in Autonomous machines, Unmanned vehicles

    Specifications

    Item Parameter Unit
    Gyro performance
    Input Range 400 dps
    Bandwidth 200 Hz
    Scale factor 20000 LSB/°/s
    Scale factor non-linearity 200 ppm
    Scale factor temp drift (1б) 500 ppm
    Bias Instability 1 deg/hr
    Bias stability (10s 1σ) 5 deg/hr
    Bias stability (1s 1σ) 15 deg/hr
    Angular Random Walk 0.25 °/√h
    Bias Run-Run (1σ) 5 deg/hr
    Accelerometer performance
    Range 10 40 g
    Nonlinearity 0.1 1.3 % FSR
    Cross Axis Sensitivity 1 1 %
    Bandwidth 2.4 2.4 Hz
    Bias Repeatability 5 5 mg
    Bias Temp Coefficient <0. 5 <0. 5 mg/°C
    Factor Scale Repeatability <0.1 0.2 %
    Factor Scale Temp Coefficient ±0.01 ±0.01 %/°C
    Factor Scale 800000 200000 μg/LSB
    System Performance
    Supply Voltage 6~12V
    Supply Consumption 2W
    Interface RS422
    Vibration 6.06g (10~2000Hz)
    Shock 5000g, 0.1ms
    Operate Temp -40℃~+ 80℃
    Storage Temp -55℃~ + 105℃
    Weight ≤100g (without shell)

    ≤220g (with shell)

    Size 43.2mm*43.2mm*35.5mm (without shell)

    65mm*70mm*45.5mm (with shell)


    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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