Haywood S. Satz, Duncan B. Cox, Jr., Ronald L. Beard, and G. Paul Landis

Peer Reviewed

Abstract: This paper describes the design and simulation of an integrated GPS/INS that accomplishes space vehicle navigation and attitude estimation. The simulation contains models of an inertial measurement unit (IMU), a GPS receiver processing signals from an array of antennas placed on the spacecraft structure, and an integrated navigation filter. Interferometric equations are employed to process GPS carrier accumulated-phase measurements from precise antenna locations in the user vehicle. Vehicle orientation in inertial space is then obtained by relating baseline-difference phase measurements to orientations of antenna baselines relative to satellite line-of-sight vectors. The method of GPS-aided attitude estimation described herein is distinguished from other methods in that it does not employ search algorithms to resolve the carrier phase cycle ambiguity. Instead, the ambiguity is modeled as a random process and is included as an error state of a statistical filter. As a result, the attitude estimation time history evolves directly for any dynamic environment.
Published in: NAVIGATION, Journal of the Institute of Navigation, Volume 38, Number 3
Pages: 273 - 284
Cite this article: Satz, Haywood S., Cox, Duncan B., Jr.,, Beard, Ronald L., Landis, G. Paul, "GPS INERTIAL ATTITUDE ESTIMATION VIA CARRIER ACCUMULATED - PHASE MEASUREMENTS", NAVIGATION, Journal of The Institute of Navigation, Vol. 38, No. 3, Fall 1991, pp. 273-284.
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