Single-Aperture GPS-based Attitude (GPS/A) Sensor for Spin-Stabilized Platforms

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$600,000.00
Award Year:
2009
Program:
SBIR
Phase:
Phase II
Contract:
NNX09CA54C
Award Id:
88024
Agency Tracking Number:
074476
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
6800 Cortona Drive, Goleta, CA, 93117
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
054672662
Principal Investigator:
KenanEzal
Principal Investigator
(805) 968-6787
kezal@toyon.com
Business Contact:
MarcellaLindbery
Business Official
(805) 968-6787
mlindbery@toyon.com
Research Institute:
n/a
Abstract
Attitude determination of spin-stabilized platforms is especially challenging. Current low-cost gyroscope technology does not lend itself to attitude determination of platforms spinning in excess of one rotation per second. Traditional GPS-based attitude (GPS/A) sensors require three or more antenna elements separated by large baselines. Single-element designs require extensive calibration of the satellite signal-to-noise ratio (SNR) and are not very accurate. Toyon Research Corporation proposes to develop a small, single-aperture low-cost GPS/A sensor for space launch vehicles, and to demonstrate the sensor in an operational environment. The sensor determines the platform attitude with a single GPS antenna having a diameter of approximately 6.5 cm. The standalone performance of Toyon's GPS/A sensor on a spinning platform is better than 2.1 degrees for roll, and better than 1.2 degrees for yaw and pitch (one-sigma). The system performance can be further improved when integrated with accelerometers and/or magnetometers. Although current low-cost gyroscope technology does not allow their use on spinning platforms, non-spinning platforms may take advantage of gyro measurements for further improvements in attitude performance. During the proposed Phase II program Toyon will develop, build and test a prototype system that will be delivered for validation onboard an actual space launch vehicle.

* information listed above is at the time of submission.

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