Precision GPS orbit determination strategies for an earth orbiter and geodetic tracking systemData from two 1985 GPS field tests were processed and precise GPS orbits were determined. With a combined carrier phase and pseudorange, the 1314-km repeatability improves substantially to 5 parts in 10 to the 9th (0.6 cm) in the north and 2 parts in 10 to the 8th (2-3 cm) in the other components. To achieve these levels of repeatability and accuracy, it is necessary to fine-tune the GPS solar radiation coefficients and ground station zenith tropospheric delays.
Document ID
19890025317
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lichten, Stephen M. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Bertiger, Willy I. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Border, James S. (California Institute of Technology Jet Propulsion Laboratory, Pasadena, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
Space Communications, Spacecraft Communications, Command And Tracking