Miniaurizable, High Performance, Fiber-Optic Gyroscopes for Small Satellites

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$124,930.00
Award Year:
2012
Program:
STTR
Phase:
Phase I
Contract:
NNX12CG14P
Agency Tracking Number:
110208
Solicitation Year:
2011
Solicitation Topic Code:
T4.01
Solicitation Number:
n/a
Small Business Information
Intelligent Fiber Optic Systems Corporation
2363 Calle Del Mundo, Santa Clara, CA, -
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
877452664
Principal Investigator:
Joey Costa
Principal Investigator
(408) 565-9000
jc@ifos.com
Business Contact:
Behzad Moslehi
Business Official
(408) 565-9004
bm@ifos.com
Research Institution:
University of Alabama in Huntsville
Gang Wang
Office of the Bursar, UC Room 2`4
Huntsville, AL, 35899-5050
() -
Domestic nonprofit research organization
Abstract
Small satellites require much lighter weight, smaller, and long life Attitude control components that can withstand stressing launch conditions and space vibration environments without compromising their performance. In particular, rate sensors that can provide high-resolution Line of Sight (LOS) stabilization, accurate inertial pointing and higher bandwidths are needed to support attitude and position determination from highly compact and very lightweight packages. IFOS, with a team having many years of pioneering experience in innovative Fiber-Optic Gyroscopes (FOGs), proposes to develop an advanced miniaturizable FOG based on an approach that would allow utilizing drastically reduced size components packageable into high performance attitude control sensor affording high degree of robustness against the shock and vibration that would maintain long term alignment in requisite space environment. IFOS will exploit novel techniques including new fiber components and coil production methods suitable for shorter wavelength operation, and vibration damping concepts that would be compatible with weight of less than 2 lb and volume under 150 cm3 for an Inertial reference Unit (IRU). Phase I will focus on feasibility study of the concept for 1-axis gyro, demonstration of critical components and simulation of vibration damping techniques needed to protect the sensor during launch and long term operation.

* information listed above is at the time of submission.

Agency Micro-sites

US Flag An Official Website of the United States Government