In the Earth-centered Velocity-Normal-Conormal (VNC) coordinate system, the Sun is in constant motion. Therefore, a Sun-pointing spacecraft will be in constant rotation relative to the Earth-centered VNC coordinate system. Because an individual Bumper run requires a fixed attitude, analyzing an extended period of time in constant rotation results in a large number of attitudes to be individually run in Bumper. This creates a need for a defined process for selecting appropriate attitudes to assess. An investigation into the mechanics driving attitude revealed patterns that can be leveraged to obtain the optimum attitudes to maximize fidelity while minimizing the number of Bumper runs. A key parameter to these patterns is Beta Angle, the angle between the orbit plane and Sun vector.
Process for Sun-Pointing Attitude in Earth Orbit
2025-03-14
Report
No indication
English
Astrodynamics , ORDEM , MMOD , Bumper
Three‐axis global magnetic attitude control of earth‐pointing satellites in circular orbit
British Library Online Contents | 2017
|Attitude stability of earth-pointing satellites
AIAA | 1965
|Attitude stability of earth pointing satellites
AIAA | 1964
|