Abstract
AbstractPrecise orbit determination (POD) is the procedure for determining the orbit of a satellite with high accuracy. Compared with global navigation satellite systems (GNSS), the low Earth orbit...
Highlights
The low Earth orbit (LEO) satellites, including CubeSats, have an orbital altitude that ranges from 300 to 1,500 km. They are used in different space missions, including satellite gravimetry, interferometric synthetic aperture radar (In-SAR), global navigation satellite systems (GNSS) radio occultation, satellite altimetry, global Earth mapping and monitoring, formation flying, and positioning using megaconstellations
One procedure, which is used in the GHOST (GPS high precision orbit determination software tools) package, starts with computing solar radiation pressure (SRP) and drag accelerations using simple models (Table 1), adjusts scale factors for these accelerations during the orbit determination, and estimates the piecewiseconstant empirical accelerations for the predefined subintervals to compensate for model deficiencies
Real-Time GNSS Precise Orbits and Clocks One of the recent advancements of Precise point positioning (PPP) is the availability of realtime GNSS precise orbit and clock corrections that can be provided by geostationary (GEO) satellites
Summary
The low Earth orbit (LEO) satellites, including CubeSats, have an orbital altitude that ranges from 300 to 1,500 km. The reduced-dynamic POD, can benefit from both sides, i.e., the availability of dynamic models, as well as GNSS observations In this method, the initial conditions, force model parameters, and possible stochastic accelerations are estimated instead of the epochwise LEO positions in the kinematic POD. One procedure, which is used in the GHOST (GPS high precision orbit determination software tools) package, starts with computing SRP and drag accelerations using simple models (Table 1), adjusts scale factors (coefficients) for these accelerations during the orbit determination, and estimates the piecewiseconstant empirical accelerations for the predefined subintervals to compensate for model deficiencies Another possible procedure, e.g., that used in the Bernese GNSS software, is based on different parameterizations of the stochastic parameters in the different processing steps of the reduced-dynamic POD procedures. The validation methods discussed in the “Kinematic POD Solution and Validation” section can be used to validate the final reduced-dynamic orbit
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