LN-200S Inertial Measurement Unit
Northrop Grumman Space Systems
Fiber-optic inertial measurement unit for space applications with flight heritage on Mars rovers and deep-space probes.
Typed specifications43 values
Discloses 10 of 11 fields engineers filter by in this category (category median 3).
- Gyro range
- 1 000 °/s datasheet p.2 1 000 °/s max · dynamic range (max)
- Mass
- 748 g typ. · datasheet p.2 748 g | 748 g 1.65 lb
- Bias instability
- 1 °/h 1s · datasheet p.2
- Envelope (L×W×H)
- Diameter: 3.5 in. (8.89 cm) Height: 3.35 in. (8.51 cm) datasheet p.2
- Output data rate
- 400 Hz data rate · datasheet p.2
- Angle random walk
- 0.07 °/√h max · datasheet p.2 0.07 °/√h max · angle random walk
- Supply voltage
- 15 V nom. · ±15 Vdc · datasheet p.2 5 V nom. · ±5 Vdc | 15 V nom. · regulated at +/-15 Vdc | 5 V nom. · regulated at +/-5 Vdc
- Power consumption
- 12 W nominal · datasheet p.2 12 W nom.
- Data interface
- RS-422/485 serial data datasheet p.2 RS-422 RS-422/485 serial data | RS-485 RS-422/485 serial data
- Operating temperature
- -54–71 °C operating · datasheet p.2 -54–71 °C temperature range
- Design lifetime
- 15 years datasheet p.1 15 years max · missions lasting up to 15 years
- Unit type
- IMU (gyros + accelerometers) three fiber-optic gyros and three MEMS accelerometers · datasheet p.1
- Gyro technology
- FOG solid-state fiber-optic gyros · datasheet p.1
- Axes
- 3 three solid-state fiber-optic gyros · datasheet p.1
- Survival temperature
- -62–85 °C survival temp range · datasheet p.2
- Random vibration
- 15 g RMS random (survival) · datasheet p.2
- Flight heritage
- The LN-200S IMU has been utilized and is still performing on the NASA Mars rovers after more than 10 years. The first prototype LN-200S was qualified for space flight onboard the Clementine spacecraft. Many spacecraft now depend on the IMU to provide reli datasheet p.1
- Missions flown
- 40 000 datasheet p.2
- Quasi-static load
- 40 g Max Input Accel · datasheet p.2
- Shock qualification
- 1 500 g 1,500 g/1,000 Hz · datasheet p.2 400 g 400 g/100 Hz
- Accelerometers included
- yes three solid-state silicon MEMS accelerometers · datasheet p.1
- Performance grade
- other medium accuracy IMU class · datasheet p.1
- Bias repeatability
- 1 °/h gyro bias repeatability, 1 sigma · datasheet p.2
- Scale factor error
- 300 ppm accelerometer scale factor accuracy, 1 sigma · datasheet p.2 100 ppm gyro scale factor stability
- Bandwidth
- 200 Hz 400 Hz data rate · datasheet p.2
- Output format
- delta angle (incremental) selectable delta theta output · datasheet p.1 delta velocity (incremental) selectable delta velocity output
- Accelerometer range
- 40 g max input accel · datasheet p.2
- Velocity random walk
- 35 m/s/√h accelerometer noise · datasheet p.2
Each value is typed with its unit and measurement condition and cites the datasheet page it was taken from. Nothing is guessed: a field that is absent here has not been published by the manufacturer. machine-extracted ✓ checked by NewSpace Market ✓ manufacturer confirmed by the manufacturer.
As published by the supplier10 lines, in the manufacturer's own wording
- Gyro bias repeatability
- 1°/hr, 1σ
- Angle random walk
- <0.07°/√hr
- Accelerometer bias repeatability
- 300 µg, 1σ
- Dynamic range (max)
- 1,000°/sec
- Power
- 12 W nominal, regulated ±5 Vdc and ±15 Vdc
- Dimensions
- 3.5 in. diameter x 3.35 in. height (8.89 x 8.51 cm)
- Mass
- 1.65 lb (748 g)
- Operating temperature
- -54°C to +71°C operating
- Electrical interface
- RS-422/485 serial data
- Enclosure
- Hermetically sealed
About
The LN-200S is a small, lightweight, highly reliable fiber-optic inertial measurement unit (IMU) built by Northrop Grumman for space applications. It comprises three solid-state fiber-optic gyros and three solid-state silicon MEMS accelerometers in a compact, hermetically sealed package that outputs incremental velocity and angle data over a digital serial bus.
Part of the LN-200 family in high-rate production since 1994 (over 40,000 units produced), the LN-200S has flown on NASA’s Mars rovers (Spirit, Opportunity, Curiosity, Perseverance), Deep Space 1, Hayabusa2, Kepler and WISE space telescopes, and numerous GEO/LEO satellites. It supports missions lasting up to 15 years and provides highly reliable attitude reference and acceleration data for spacecraft attitude control systems.
Documentation
- LN-200S-LN-200HPS-inertial-measurement-unit-imu-datasheet_Original file.pdf PDF source: media.northropgrumman.com ↗
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