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Improvements in Nonconservative Force Modelling for TOPEX/POSEIDONIt was recognized prior to the launch of TOPEX/POSEIDON, that the most important source of orbit error other than the gravity field, was due to nonconservative force modelling. Accordingly, an intensive effort was undertaken to study the nonconservative forces acting on the spacecraft using detailed finite element modelling (Antreasian, 1992; Antreasian and Rosborough, 1992). However, this detailed modelling was not suitable for orbit determination, and a simplified eight plate "box-wing" model was developed that took into account the aggregate effect of the various materials and associated thermal properties of each spacecraft surface. The a priori model was later tuned post launch with actual tracking data [Nerem et al., 1994; Marshall and Luthcke, 1994; Marshall et al., 1995]. More recently, Kubitschek (1997] developed a newer box-wing model for TOPEX/POSEIDON, which included updated material properties, accounted for a solar array deflection, and modelled solar array warping due to thermal effects. We have used this updated model as a basis to retune the macromodel for TOPEX/POSEIDON, and report on preliminary results using at least 36 cycles (one year) of SLR and DORIS data in 1993.
Document ID
19990114245
Acquisition Source
Goddard Space Flight Center
Document Type
Conference Paper
Authors
Lemoine, Frank G.
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Rowlands, David D.
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Chinn, Douglas S.
(Raytheon Co. Greenbelt, MD United States)
Kubitschek, Daniel G.
(Colorado Univ. Boulder, CO United States)
Luthcke, Scott B.
(Raytheon Co. Greenbelt, MD United States)
Zelensky, Nikita B.
(Raytheon Co. Greenbelt, MD United States)
Born, George H.
(Colorado Univ. Boulder, CO United States)
Date Acquired
August 19, 2013
Publication Date
January 1, 1999
Subject Category
Oceanography
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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