High Performance Navigation MEMS IMU

ER-MIMU-052
1. Size: 70*65*45(with shell)/43.2*43.2*35.5 (without shell and baseboard);
2. OEM, modular design, strong applicability;
3. Gyro bias instability(1σ 25℃): 0.03deg/hr.

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Introduction

ER-MIMU-052 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-052 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
Size:70*65*45(with shell)/43.2*43.2*35.5 (without shell and baseboard)
Weight:220(with shell) /100(without shell and baseboard)
OEM, modular design, strong applicability
-40~80°C temperature compensation
Gyro bias instability: 0.03deg/hr
Gyro bias stability (10s 1σ): <0.15deg/hr
Gyro angular random walk: <0.01 °/√h
Accelerometer bias repeatability: 100ug
Accelerometer class II non-linearity coefficient: <100ug/g²
High-performance navigation

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	A	B
Range	300	400	deg/s
Scale Factor at 25°C	28000	20000	LSB/deg/s
Scale Factor Repeatability (1σ)	<50	<20	ppm
Scale Factor VS Temperature (1σ)	300	100	ppm
Scale Factor Non-Linearity (1σ)	<300	<100	ppm
Bias Instability(1σ 25℃)	0.03	0.03	deg/hr
Bias stability (10s 1σ)	<0.15	<0.5	deg/hr
Angular Random Walk	<0.01	<0.025	°/ √h
Bias Repeatability(1σ 25℃)	<0.3	<0.15	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 and baseboard)		mm
Weight	≤220(withshell) ≤100(without shell and baseboard)		g