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Session B11: Inertial Navigation Technologies

HG3900 All-Silicon MEMS Near-Navigation Grade Inertial Measurement Unit with Demonstrated RLG Stability
Mark Sawyer, Honeywell International
Location: Ballroom E
Date/Time: Wednesday, Jun. 4, 4:05 p.m.

Honeywell Aerospace Technologies has developed next generation near-navigation grade micro-electromechanical systems (MEMS) gyroscopes and accelerometers and has successfully integrated those sensors into a new, near-navigation grade inertial measurement unit (IMU) in a small size, weight, and power (SWaP) form-factor. This new IMU, called the HG3900, demonstrates the next major milestone in groundbreaking MEMS IMU technology, as Honeywell continues to create innovative navigation grade MEMS inertial sensors.
The HG3900 IMU consists of three next generation out-of-plane all-silicon MEMS gyroscopes and three MV60 all-silicon MEMS accelerometers. All sensors are Honeywell’s own design and are fabricated in our Plymouth, Minnesota foundry, sharing production with the high volume HG1930 IMU sensors. These sensors have evolved from DARPA’s Precise Robust Inertial Guidance for Munitions: Navigation-Grade Inertial Measurement Unit (PRIGM: NGIMU) program. The sensors are integrated with an internal proprietary environmental vibration and shock isolation system, electronics, and microprocessor within a robust and compact package to realize the full IMU system. Comprehensive IMU performance results will be provided from a large quantity of recent prototypes.
The gyro performance characterization at the IMU level is based on extensive testing of the recent prototypes over the full -54°C to +85°C specified operating temperature range and it shows that the sensors exhibit high-rate capability combined with industry-leading low noise operation as well as excellent bias stability. The IMUs are demonstrating gyro performance with a bias total RMS of better than 0.3°/hr, scale factor better than 300ppm, angular random walk (ARW) of better than 0.008°/?hr, and a bias in-run stability of better than 0.1°/hr. This performance demonstrates that the IMU is a very capable, lower SWaP solution compared to tactical ring laser gyro (RLG) and fiber optic gyro (FOG) based IMUs, and shows that MEMS inertial sensors can perform to those levels.
The accelerometer performance via the integrated Honeywell MV60 accelerometers demonstrates the acceleration channel of the IMU performs to near-navigation grade. As expected, the scale factor and vibration performance in the HG3900 are outstanding.
This presentation will highlight the technical progress made in developing near-navigation grade all silicon MEMS inertial sensors into a fully capable HG3900 IMU prototype. A sampling of the extensive performance testing results will be shown in addition to plans to further enhance and qualify the design into full rate production.

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