Low-Cost Attitude-Control MEMS IMU

ER-MIMU-04/04Mini
1. New mini version: 40*40*42mm(with shell)/27*26*34(without shell and baseboard);
2. -40~80°C temperature compensation;
3. OEM modular design, strong applicability.

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Introduction

ER-MIMU-04/04Mini 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-04/04Mini uses MEMS accelerometer and gyroscope with high quality and reliability, RS422 and external communication. Default baud rate 921600 (customized). 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.

A simple operation is required to connect our products to your system and obtain IMU data without the 15-pin plug provided by our company. At the same time, the size and weight of our products can be significantly reduced by removing the base plate housing.

Features
New mini version size: 40*40*42(mini version with shell)/27*26*34(mini version without shell and baseboard)
Weight: 80g(mini version with shell)/ 40g(mini version without shell and baseboard)
OEM modular design, strong applicability
-40~80°C temperature compensation
The product is low-cost
Gyro bias instability: 1deg/hr
Gyro bias stability (10s 1σ): 5deg/hr
Gyro angular random walk: 0.25 °/√h
Accelerometer bias repeatability: 100ug
Accelerometer bias stability (10s) (1σ): <50ug
Accelerometer class II non-linearity coefficient: <100ug/g2

Application
Robotic control & orientation in autonomous machines, unmanned vehicles
Azimuth, attitude, position measuring and keeping in GNSS-assisted INS
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 system
Stabilizing & Pointing in satellite antenna, target tracking system

Specifications

Item	Parameter		Unit
Gyro performance	A	B	/
Range	400	400	deg/s
Scale Factor at 25°C	20000	20000	LSB/deg/s
Scale Factor VS Temperature (1σ)	±500	±500	ppm
Scale Factor Non-Linearity (1σ)	<200	200	ppm
Bias Instability (1σ 25℃)	1	1	deg/hr
Bias Stability (10s 1σ)	5	4	deg/hr
Angular Random Walk	<0.25	<0.2	°/ √h
Bias Repeatability (1σ 25℃)	5	4	deg/hr
Accelerometer performance
Range	30		g
Bias Stability (10s 1σ)	<50		ug
Bias Repeatability	100		ug
Bias Temp Coefficient	<20		ug/℃
Bias Temp Hysteresis	<1.5		mg
Scale Factor Non-linearity	<500		ppm
Scale Factor Repeatability	<30		ppm
Scale Factor Temp Coefficient	10		ppm/℃
Class II Non-linearity Coefficient	<100		ug/g2
Scale Factor	250000		Lsb/g
Environment and power
Operate temperature	-40~+80		℃
Storage temperature	-55~+105		℃
Power supply	6~12V		V
Power (power supply 6V)	2		W
Communication interface	RS-422
Physical characteristics
Size	70×65×45(with shell)43.2×43.2×35.5 (without shell and baseboard) 404042(mini version with shell)/272634(mini version without shell and baseboard)		mm
Weight	≤220(withshell) ≤100(without shell and baseboard) 80g(mini version with shell)/ 40g(mini version without shell and baseboard)		g