Low-Cost Attitude-Control MEMS IMU

ER-MIMU-04
1. Gyro bias instability: 1 deg/hr;
2. Gyro Bias stability (10s 1σ):5deg/hr;
3. Gyro angular random walk:0.25°/√h;
4. 3 axis gyroscope & 3-axis accelerometer.

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Introduction

ER-MIMU-04 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.

Features
Gyro bias instability:1deg/hr
Gyro bias stability (10s 1σ): 5deg/hr
Gyro angular random walk:0.25 °/√h
Weight：≤100g (without shell)
≤220g (with shell)
Operate Temp：-40℃~ + 80℃
The product is low-cost and can be gesture controlled
small size

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	43.2mm43.2mm35.5mm (without shell) 65mm70mm45.5mm (with shell)