referansebane
Referansebane is a concept used in space mission design and operations to denote a nominal, mathematically defined orbital path against which the spacecraft’s actual trajectory is measured. The referansebane serves as the baseline orbit chosen during mission design to satisfy mission requirements and to provide a reference for navigation, trajectory planning, and performance assessment. It is specified by standard orbital elements—the semi-major axis (a), eccentricity (e), inclination (i), longitude of the ascending node (Ω), argument of periapsis (ω), and the true anomaly or epoch—describing the orbit at a given reference time.
In operations, the referansebane provides the target for maneuvers and the yardstick for deviation: the current
The referansebane is distinct from the actual operational orbit, which is the real, evolving trajectory. It