Low-cost Attitude-control MEMS IMU

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

Low-cost Attitude-control MEMS IMU

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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

ItemParameterUnit
Gyro performance
Input Range400dps
Bandwidth200Hz
Scale factor20000LSB/°/s
Scale factor non-linearity200ppm
Scale factor temp drift (1б)500ppm
Bias Instability1deg/hr
Bias stability (10s 1σ)5deg/hr
Bias stability (1s 1σ)15deg/hr
Angular Random Walk0.25°/√h
Bias Run-Run (1σ)5deg/hr
Accelerometer performance
Range1040g
Nonlinearity0.11.3% FSR
Cross Axis Sensitivity11%
Bandwidth2.42.4Hz
Bias Repeatability55mg
Bias Temp Coefficient<0. 5<0. 5mg/°C
Factor Scale Repeatability<0.10.2%
Factor Scale Temp Coefficient±0.01±0.01%/°C
Factor Scale800000200000μg/LSB
System Performance
Supply Voltage6~12V
Supply Consumption2W
InterfaceRS422
Vibration6.06g (10~2000Hz)
Shock5000g, 0.1ms
Operate Temp-40℃~+ 80℃
Storage Temp-55℃~ + 105℃
Weight≤100g (without shell)

≤220g (with shell)

Size43.2mm*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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