High Performance Navigation MEMS IMU

ER-MIMU-02/02Mini
1. New mini version: 40*40*42mm(with shell)/27*26*34(without shell);
2. The inner platform body adopts the design of China Ding, with high reliability;
3. Gyro bias instability(1σ 25℃): 0.05deg/hr.

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Introduction

ER-MIMU-02/02Mini High Performance Navigation MEMS IMU

Introduction
Inertial Measurement Unit (IMU) is a device that measures an object's three-axis attitude angle (or angular velocity) and acceleration. Gyroscopes and accelerometers are the core devices of an Inertial Navigation System (INS). Through the built-in accelerometers and gyroscopes, the IMU can measure the three-axis linear acceleration and three-axis rotational angular velocity, and obtain the attitude, velocity, and displacement information of the carrier through analysis.

ER-MIMU-02/02Mini uses MEMS accelerometer and gyroscope with high quality and reliability, RS422 and external communication.Default baud rate 921600 (customized), 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.

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)
Weight: 120g(mini version with shell)/ 80g(mini version without shell)
OEM, modular design, strong applicability
-40~80°C temperature compensation
Gyro bias instability: 0.05deg/hr
Gyro bias stability (10s 1σ): <0.5deg/hr
Gyro angular random walk: <0.025 °/√h
Accelerometer bias repeatability: 100ug
Accelerometer class II non-linearity coefficient: <100ug/g2
High-performance navigation
Weight: ≤100g (without shell)/≤220g (with shell)

Application
Integrated Navigation Systems & Inertial Guidance System
Flight Control System
Attitude Heading Reference Systems (AHRS)
Stabilization of Antennas, Cameras & Platforms
Aerial and Marine Geo-mapping / Surveying

Specifications

Item	Parameter	Unit
Gyro performance
Range	400	deg/s
Scale Factor at 25°C	20000	LSB/deg/s
Scale Factor Repeatability (1σ)	<20	ppm
Scale Factor VS Temperature (1σ)	±100	ppm
Scale Factor Non-Linearity (1σ)	<100	ppm
Bias Instability (1σ 25℃)	0.05	deg/hr
Bias Stability (10s 1σ)	<0.5	deg/hr
Angular Random Walk	<0.025	°/ √h
Bias Repeatability (1σ 25℃)	<0.3	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 Month 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 DC	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) 404042(mini version with shell)/272634(mini version without shell)	mm
Weight	≤220(withshell) ≤100(without shell) 120g(mini version with shell)/ 80g(mini version without shell)	g