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ER-MIMU-M02 High Performance MEMS IMU
Introduction
The ER-MIMU-M02 is an inertial measurement unit (IMU) based on micro-mechanical technology (MEMS), including a built-in MEMS gyroscope with 2°/h (Allan) bias stability and a MEMS accelerometer with 100 µg (Allan) bias stability, three-axis magnetometer and barometer.
It is a device that measures the three-axis attitude angle (or angular rate) and acceleration of an object. Gyroscope and accelerometer are the core devices of inertial navigation system. With a built-in acceleration sensor and gyroscope, the MEMS IMU measures linear acceleration and rotational angular rate from three directions, which can be solved to obtain information such as carrier attitude, speed and displacement. Magnetometers help with orientation and can be used to calibrate and direct data to the correct location.
The product has high reliability and strong environmental adaptability. That is, it can be widely used in fields such as drones, smart bombs, seekers, rocket shells and stable platforms.
Features
Three-axis digital gyroscope:
Dynamic measurement range of ±450º/s;
Bias instability: 2 º/h (Allan variance);
Angular Random Walk: 0.1º/√h.
Three-axis digital accelerometer:
Dynamic measurement range: 18g;
Bias stability: 0.1mg (Allan variance);
Angular Random Walk: 0.02m/s√h;
High reliability: mean time between failures>20000h;
Ensure the accuracy within the full temperature range (-40℃~75℃): Built-in high-performance temperature calibration and compensation algorithm;
Support stable platform application: full parameter measurement and measurement bandwidth>100Hz;
Interface includes 1-channel SPI and 1-channel UART.
Specifications
| Parameter | Test condition | Min value | Typical value | Max value | Unit |
| Gyroscope | |||||
| Dynamic measurement range | / | ±400 | ±450 | º/s | |
| Bias stability | Allan variance | / | 2 | / | º/h |
| Angular Random Walk | / | / | 0.1 | º/√h | |
| Bias repeatability | Full temperature | / | ±0.1 | 0.2 | º/s |
| Scale factor repeatability | Full temperature | / | 0.5 | 1 | % |
| Scale factor non-linearity | FS=450 º/s | / | 0.1 | 0.2 | %FS |
| Bandwidth | / | / | / | 400 | Hz |
| Accelerometer | |||||
| Dynamic measurement range | / | / | 18 | / | g |
| Bias stability | / | 0.1 | / | mg | |
| Angular Random Walk | / | / | 0.02 | 0.02 | m/s/√h |
| Bias repeatability | Full temperature | / | 10 | 32 | mg |
| Scale factor repeatability | Full temperature | / | ±0.5 | ±1 | % |
| Scale factor non-linearity | FS=16g | / | 0.2 | / | %FS |
| Bandwidth | / | / | / | 200 | Hz |
| Magnetometer | |||||
| Dynamic measurement range | / | / | ±2 | / | gauss |
| Sensitivity | / | / | 0.1 | / | mgauss/LSB |
| Initial sensitivity error | / | / | 2 | / | % |
| Sensitivity temperature coefficient | / | / | 250 | / | ppm/℃ |
| Non-linearity degree | / | / | / | 1 | % of FS |
| Initial bias error | / | / | 400 | / | mgauss |
| Partial temperature coefficient | / | / | 0.7 | / | mgauss/℃ |
| Output noise | / | / | 4 | / | mgauss |
| Noise density | / | / | 1 | / | mgauss/√Hz |
| Bandwidth | / | / | 50 | 200 | Hz |
| Barometer | |||||
| Pressure range | extension | 450 | / | 1100 | mbar |
| 50 | / | 1200 | mbar | ||
| Overall error | / | / | 6.0 | / | / |
| Long-term stability | / | / | 1 | / | mbar/year |
| Communication interface | |||||
| 1 way SPI | Baud rate | / | / | 15 | MHz |
| 1 way UART | Baud rate | 9.6 | 230.4 | 921.6 | Kbps |
| Electrical specification | |||||
| Voltage | / | 3 | 3.3 | 3.6 | V |
| Power dissipation | / | / | / | 1.5 | W |
| Ripple wave | P-P | / | / | 10 | mV |
| Structural characteristics | |||||
| Dimension | 47×44×15mm | ||||
| Weight | / | 41 | 42 | 47 | g |
| Operating environment | |||||
| Operating temperature | / | -40 | 75 | ℃ | |
| Storage temperature | / | -45 | 80 | ℃ | |
| Vibration | / | / | 3g, 10~2000Hz | / | / |
| Impact | / | / | 30g, 11ms | / | / |
| Mean time between failures | / | / | 20000 | / | h |
| Reliability | |||||
| Continuous working hours | / | / | 120 | / | h |
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
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