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Precision orbit determination for the TOPEX/Poseidon missionComputation of precise orbits for the TOPEX/Poseidon (T/P) spacecraft is analyzed focusing on gravity field modeling, nonconservative force modeling, satellite tracking technologies, and orbit determination software. It was found that the radial orbit error budget for T/P allows 10 cm rms error due to gravity field mismodeling, 3 cm due to solid earth and ocean tides, and 6 cm due to radiative forces, and 3 cm due to atmospheric drag. It is concluded that the current models are capable of achieving the radial orbit error requirements.
Document ID
19920069440
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nerem, R. S. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Marshall, J. A. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Putney, B. H. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Pavlis, E. C. (Maryland, University College Park, United States)
Klosko, S. M. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Williamson, R. G. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Zelensky, N. P. (Hughes STX Corp. Lanham, MD, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Astrodynamics
Report/Patent Number
AIAA PAPER 92-4433
Report Number: AIAA PAPER 92-4433
Meeting Information
Meeting: 1992 AIAA/AAS Astrodynamics Conference
Location: Hilton Head Island, SC
Country: United States
Start Date: August 10, 1992
End Date: August 12, 1992
Accession Number
92A52064
Distribution Limits
Public
Copyright
Other

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