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.
Precision orbit determination for the TOPEX/Poseidon mission
1992 AIAA/AAS Astrodynamics Conference ; 1992 ; Hilton Head Island, SC, United States
01.01.1992
Aufsatz (Konferenz)
Keine Angabe
Englisch
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