Description: We propose a new approach for to the design and fabrication of miniaturized Interferometric Fiber Optical Gyroscope (FOG) that enables the production of smaller IRU with enhanced performance. The size and performance limitations of the standard FOG are being reduced due to the utilization of highly integrated approach of all the gyro components. Specifically, the ASE light source and the receivers, splitters and TIA are all incorporated in a small, robust silicon/silica platform using hybrid integration. In addition, the sensor is using an innovative new coil design and high performance miniaturized IOC that results in tenfold reduction of the bias temperature sensitivity compared to the existing FOG products. The combination of these attributes supports a smaller, lower cost, high performance and robust IRU that can serve future NASA mission needs.

Benefits: The proposal will develop the key enabling component in a low cost, high precision inertial navigations system (< 0.01 deg/hr accuracy). Low cost, higher precision and low weight/power (SWaP) inertial sensors are necessary components for future NASA spacecraft guidance, navigation, and control technologies. The proposed technology will also find application in Unmanned Aircraft Systems (UAS), Sounding Rocket and many other Autonomous missions as key technologies that have in NASA technology roadmap.

The Navigational and high-end tactical IMU market is an expanding market with a push for improved performance. This expansion will be driven by cost and size reduction. The proposed technology will be the smallest volume IRU/IMU on the market today. It will enable new commercial and DoD applications including airborne PODs, Line of Sight stabilization, weapon designation, Interceptor technology, individual soldier navigation, battlefield management, turret stabilization, missiles, UAV, AHARS and more.