ER-AHRS-10 IMU/VRU/AHRS
Introduction
The ER-AHRS-10 inertial sensing system integrates industrial-grade MEMS gyroscope and accelerometer, which can output 3D angular velocity, acceleration, magnetic field information, and fused 3D azimuth angles.When connected to a satellite navigation (GNSS) signal, fused position and velocity information can be output. ER-AHRS-10 includes ER-AHRS-10U Inertial Measurement Unit (IMU), ER-AHRS-10V Vertical Reference System (VRU), ER-AHRS-10A Attitude Reference System (AHRS)
The ER-AHRS-10 is embedded with multi-sensor fusion algorithm, which has been calibrated at the factory in all temperature ranges to ensure the excellent performance of the system in harsh environments. The compact design of the ER-AHRS-10 makes it easy for customers to integrate applications and shorten the development cycle.
The ER-AHRS-10 has a dynamic attitude detection accuracy of 0.3° and provides a stable, low-drift relative heading output and a drift-free absolute heading output. It can meet the attitude, direction stability control, positioning and navigation needs of various carriers in complex and harsh application environments.
Features
Stable heading output
3 ° dynamic attitude accuracy
Industrial-grade inertial sensors
Gyro bias instability: 6 °/h
Accelerometer bias instability: 0.05mg
Application
Robots, unmanned vehicles
Construction machinery, intelligent agricultural machinery
Satcom on the move/Communication in Moving
Product model information
Items | ER-AHRS-10U | ER-AHRS-10V | ER-AHRS-10A |
Angular velocity, acceleration | √ | √ | √ |
Attitude angle | √ | √ | |
Relative heading angle | √ | √ | |
Absolute heading angle | √ |
Specifications:
Attitude orientation performance
Attitude angle | 0.3 ° | 1σ RMS | |
Heading angle | Relative heading angle*
Absolute heading angle** |
0.8 ° | 1σ RMS |
1 ° | 1σ RMS | ||
Sensor parameters | |||
Gyroscope | Accelerometer | Magnetic sensors | |
Range ±500 °/s | ±16g | ±8 Gauss | |
Non-linearity ±0.05%FS | ±0.5%FS | ±0.2%FS | |
Bias instability*** 6 °/h | 0.05mg | - | |
Noise density 0.015 °/s/√ Hz | 100μg/√ Hz | 0.4mG (RMS) | |
Bandwidth 116Hz | 116Hz | - | |
System parameters | |||
Input voltage 3.3- 16VDC | Size | 37.7*24*9.5mm | |
Power consumption 250mW | Weight | 15.5g | |
Operating temperature -40~85℃ | Hardware interface | SPI UART | |
Output frequency | 200Hz | ||
Note: The above parameters are typical values
* Provides a relative heading angle without reference,Regular motion drift<0.8 °/min,Static drift<0.8 °/hr。 ** In a homogeneous magnetic field environment *** Allan variance,1σ @25℃ |
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