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Session C7: Inertial Measurement Unit (IMU)

Dual-Use Navigation-Grade MEMS IMU
Burgess R. Johnson, John Reinke, Markus Gnerlich, Curt Albrecht, Todd Braman, Patrick Duffy, Daniel Endean, Honeywell International
Location: Ballroom D
Date/Time: Thursday, Aug. 26, 11:10 a.m.

The broad need for higher performance navigation in reduced size, weight, and power, especially in GPS-denied environments, is driving Honeywell’s development of higher performance MEMS inertial measurement units (IMUs). To address this need, Honeywell is developing the HG7930, a dual-use navigation-grade MEMS IMU operating over the full mil-spec temperature range of -54C to +85C. The IMU has the same electrical interface and same mechanical footprint as Honeywell’s tactical-grade HG1930 MEMS IMU. It contains 3 nav-OPG out-of-plane MEMS gyroscopes, and 3 high performance in-plane MEMS accelerometers. The gyro and accel sensors are fabricated and packaged in the same MEMS foundry as the HG1930 sensors, a feature that is expected to accelerate transition of the IMU to production. The design of the nav-OPG MEMS gyroscopes is derived from the out-of-plane gyro sensor in Honeywell’s HG1930 IMU. The frequency separation between gyro drive and sense modes is non-zero, providing wide sensor bandwidth and high fabrication yield. The gyros have bias turn-on to turn-on (TOTO) repeatability better than 0.1 deg/hr, scale factor TOTO repeatability better than 80 ppm, bias instability (minimum of Allan deviation) better than 0.02 deg/hr, and operating range greater than 900 deg/sec. Median compensated gyro bias over temperature of 0.2 deg/hr is typical. The accelerometers have typical bias TOTO repeatability of 20 micro-g, scale factor TOTO repeatability better than 25 ppm, bias instability (minimum of Allan deviation) better than 2 micro-g, and operating range greater than 60 g. Median compensated accel bias over temperature of 100 micro-g is typical. IMU bandwidth is approximately 140 Hz, where bandwidth is defined as the frequency at which the IMU output data lags the inertial inputs by 90 degrees. Nominal IMU power consumption is 3 Watts. The presentation will include IMU performance data as well as development plans to meet the shock and vibration requirements of tactical operating environments.
This work is funded internally by Honeywell and in part by the U.S. Government through DARPA’s PRIGM NGIMU program. The views and conclusions contained in this document are those of the authors and should not be interpreted as representing the official policies, either expressed or implied, of the U.S. Government. Approved for Public Release, Distribution Unlimited.



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