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Small & Redundant MEMS-IMU

MRN-01-SS (MEMS-IMU)

with Track Record of Being Adopted by JAXA!

  • Low cost

  • High precision

  • Environmental
    resistance

  • Low price

  • High precision

  • Environmental
    resistance

MRN-01-SS has developed with JAXA

We have participated in technology demonstrations and test launches conducted by JAXA.
The accuracy and reliability were confirmed during both "in-orbit demonstrations" and "flight demonstrations."

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Four key features for mission success

Small & Redundant
Inertial Sensor (IMU)
MRN-01-SS

  • Feature 1

    Low cost

    By utilizing MEMS gyroscopes and accelerometers, it offers a cost-effective alternative to space-grade FOG and RLG

  • Feature 2

    High accuracy

    Equipped with high-precision gyroscopes, it achieves accuracy comparable to FOG and RLG systems.

  • Feature 3

    Environmental
    resistance

    Designed to withstand the harsh conditions of space missions, including vibration, shock, temperature extremes, and radiation

  • Feature 4

    Redundancy

    Featuring dual independent 3-axis IMU units, ensuring reliability and redundancy for critical missions

Download the comprehensive document now
to access detailed product specifications

Technical Document

Case studies

Proven track records from demonstration experiments

1. In-orbit demonstration

Combining "commercial off-the-shelf components" and "redundant circuit technology" to overcome radiation resistance challenges

The MRN-01 was onboard Rapid Innovative payload demonstration SatellitE-2 (RAISE-2) conducted by JAXA, aiming to demonstrate a high-performance, lightweight, and low-cost redundant MEMS-IMU in orbit.

Over 426 days in orbit, data on "operation, performance, and radiation errors" was successfully collected.

Proving radiation resistance

During the demonstration period, one of the IMU units produced abnormal data twice. However, the other IMU unit continued to measure and output normal data.

This confirmed the effectiveness of the "redundant circuit configuration" and "radiation-resistant components," demonstrating their sufficient reliability for space applications.

2. Flight demonstration

Inertial sensor data was successfully collected

MRN-01 is loaded on Epsilon6 and H3 rocket test vehicles 1 and 2.
During the launch phase, inertial sensor data was successfully collected.

Main specifications of
MRN-01-SS

Size 153 × 106 × 83 mm (6.02 × 4.17 × 3.27 inches)
Weight 1.3kg
Power consumption 5W
Gyroscope performance
Measurement range : ±400 deg/s
Bias instability : 0.2 deg/h
Angle random walk : 0.051 deg/√h
Vibration rectification error : 1 deg/h/grms²
Acceleration performance
Measurement range : ±30 g
Bias instability : 90 μg
velocity random walk : 150 mm/s/√h
Bias vibration sensitivity : 0.15 mg/grms²
Data output cycle 100Hz
Output format RS422

Technical Document

We offer customized MRN-0X

Please feel free to contact us with any requests!

Example customizations

Example①

A product with a narrower measurement range tailored for satellite applications

Specification proposal of example①

Example②

A more compact product integrating a single unit (MRN-5X)

Specification proposal of example②

※Regarding customization, please check the quantity and the other conditions

Specification proposal for example①

MRN-01 MRN-01（Low-range）
Size 153 × 106 × 83 mm
(6.02 × 4.17 × 3.27 inches)		 153 × 106 × 83 mm
(6.02 × 4.17 × 3.27 inches)
Weight 1.3kg 1.3kg
Power consumption 5W 5W
Gyroscope performance
Measurement range : ±400 deg/s
Bias instability : 0.2 deg/h
Angle random walk : 0.051 deg/√h
Vibration rectification error : 1 deg/h/grms²
Measurement range : ±50 deg/s
Bias instability : 0.1 deg/h
Angle random walk : 0.02 deg/√h
Vibration rectification error : 1 deg/h/grms²
Acceleration performance
Measurement range : ±30 g
Bias instability : 90 μg
velocity random walk : 150 mm/s/√h
Bias vibration sensitivity : 0.15 mg/grms²
Measurement range : ±2.5 g
Bias instability : 10 μg(TBD)
velocity random walk : 25 mm/s/√h(TBD)
Bias vibration sensitivity : 0.15 mg/grms²
Data output cycle 100Hz 100Hz
Output format RS422 RS422

Specification proposal for example②

2 IMUs product 1 IMU product
Size 153 × 106 × 83 mm
(6.02 × 4.17 × 3.27 inches)		 88* × 106 × 83 mm
(3.46* × 4.17 × 3.27 inches) *TBD
Weight 1.3kg 0.8kg(TBD)
Power consumption 5W 2.5W
Gyroscope performance
Measurement range : ±400 deg/s
Bias instability : 0.2 deg/h
Angle random walk : 0.051 deg/√h
Vibration rectification error : 1 deg/h/grms²
Measurement range : ±400 deg/s
Bias instability : 0.2 deg/h
Angle random walk : 0.051 deg/√h
Vibration rectification error : 1 deg/h/grms²
Acceleration performance
Measurement range : ±30 g
Bias instability : 90 μg
velocity random walk : 150 mm/s/√h
Bias vibration sensitivity : 0.15 mg/grms²
Measurement range : ±2.5 g
Bias instability : 10 μg(TBD)
velocity random walk : 25 mm/s/√h(TBD)
Bias vibration sensitivity : 0.15 mg/grms²
Data output cycle 100Hz 100Hz
Output format RS422 RS422

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