NASA NTRS · 19920069440
Precision orbit determination for the TOPEX/Poseidon mission
Abstract
Computation 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.
Keep this discovery
Explore connections, maps & timelines
Nerem, R. S., Marshall, J. A., Putney, B. H., Pavlis, E. C., Klosko, S. M., Williamson, R. G., Zelensky, N. P.. 1992-01-01. Precision orbit determination for the TOPEX/Poseidon mission. https://ntrs.nasa.gov/citations/19920069440
Cite the original work for its findings. Save a collection to share your selection of sources.