Gyroscopic Inertial Micro-Balance Azimuth Locator (GIMBAL)

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX10CD77P
Agency Tracking Number: 095877
Amount: $99,968.00
Phase: Phase I
Program: SBIR
Awards Year: 2010
Solicitation Year: 2009
Solicitation Topic Code: S3.06
Solicitation Number: N/A
Small Business Information
Research Support Instruments, Inc.
4325-B Forbes Blvd., Lanham, MD, 20706-4854
DUNS: 076337877
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 John Kline
 Principal Investigator
 (732) 329-3700
 kline@researchsupport.com
Business Contact
 Christopher Rollins
Title: Vice President
Phone: (301) 306-0010
Email: rollins@researchsupport.com
Research Institution
N/A
Abstract
Research Support Instruments, Inc. (RSI) proposes the Gyroscopic Inertial Micro-Balance Azimuth Locator (GIMBAL) program to use an innovative encapsulated spinning wheel micro-gyroscope as a Guidance, Navigation, and Control (GN&C) actuator for small spacecraft use. While macro-size gyroscopes, including fiber ring gyros, have achieved navigation-grade performance, Micro-Electro-Mechanical System (MEMS) gyros have been limited to rate-grade performance, particularly in long-term bias drift. This is often attributable to quadrature error, which is a result of cross-coupling between drive and sense axes (Yazdi 1998). GIMBAL is particularly suited to addressing this, since it does not rely on the vibratory structure common in MEMS gyros. Instead, it uses a true spinning wheel for the proof mass, which will not have any mechanical linkages between axes. This will result in a bias drift much smaller than encountered in current MEMS-sized gyros. The Phase I GIMBAL program will involve design, fabrication, and test of the key encapsulated micro-gyro technology as well as system design of the GN&C component. In Phase II, the complete gyro sensor will be designed and built, and detailed tests and demonstrations will resolve design issues for the final design. The result will be a GN&C component that will address a critical need in future NASA science missions.

* information listed above is at the time of submission.

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