GPS ATTITUDE DETERMINATION FOR THE SOAR EXPERIMENT

Jaejong Um and E. Glenn Lightsey

Abstract: The first on-orbit data from the Space Integrated GPS/INS (SIGI) sensor, derived from the SIGI Orbital Attitude Readiness (SOAR) demonstration during the STS-101 mission of the Space Shuttle Atlantis in May 2000, is analyzed. The attitude estimation performance for both stand-alone GPS and integrated GPS/INS is presented. The extended Kalman filter for the GPS/INS system provided better results with differential phase measurements than with quaternion measurements. Additional studies were carried out to improve the performance of the attitude determination. First, a cold-start initialization module using signal-to-noise ratio (SNR) was developed to overcome the limitation in the integer ambiguity resolution of the current onboard algorithm that the pitch and roll angles should be less than 15 deg for successful integer search. Second, GPS-based attitude determination with line bias modeling and multipath mitigation was performed to improve the performance to be as accurate as 0.06 deg (root mean square [RMS]) in three axes.
Published in: NAVIGATION, Journal of the Institute of Navigation, Volume 48, Number 3
Pages: 181 - 194
Cite this article: Um, Jaejong, Lightsey, E. Glenn, "GPS ATTITUDE DETERMINATION FOR THE SOAR EXPERIMENT", NAVIGATION, Journal of The Institute of Navigation, Vol. 48, No. 3, Fall 2001, pp. 181-194.
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