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- W2156036212 abstract "Simulation results show that prediction of aerodynamic drag fluctuations, predominantly caused by variability in solar flux, and OD accuracy are the dominant error sources in maneuver planning for RGT maintenance. The 17:30 terminator orbit is well suited for mitigating these negative influences as it not only minimizes the variability in aerodynamic drag, but also reduces the influence of drag as a primary error source, leaving OD accuracy as the dominant parameter driving station-keeping operations. The results indicate decimeter-level OD accuracy is necessary to maintain the 1 km RGT. A maneuver strategy which maximizes the time between delta-v maneuvers, minimizes the impact to NPOESS operational availability, and maintains the required RGT is developed and tested over a recent eleven-year solar-cycle. The maneuver strategy uses both in-plane (drag-makeup) delta-v maneuvers and out-of plane delta-v inclination adjustment maneuvers (IAM) to control the required parameters of the orbit." @default.
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- W2156036212 date "2007-06-18" @default.
- W2156036212 modified "2023-09-27" @default.
- W2156036212 title "Maintaining a ±1km Repeating Ground-Track Orbit for the National Polar-Orbiting Operational Environmental Satellite System (NPOESS)" @default.
- W2156036212 cites W2048975013 @default.
- W2156036212 doi "https://doi.org/10.2514/6.2007-6102" @default.
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