Position of a body along its orbit at a given time, relative to its
parent (km, parent-centred — a moon's position is relative to its
planet, not the star; the caller composes these up the parent chain for
an absolute position — see resolveAbsolutePosition).
Standard Keplerian propagation: mean anomaly at time t -> eccentric
anomaly (solveEccentricAnomaly) -> true anomaly + radius -> position in
the orbital (perifocal) plane -> rotated into the reference frame by the
three orientation angles (inclination, ascending node, argument of
periapsis) and, when set, out of the elements' own reference plane (see
OrbitalElements.referencePlanePole). This is the same transform any orbital mechanics
reference (e.g. Vallado's "Fundamentals of Astrodynamics") gives for
classical-element propagation — not specific to any one body.
Position of a body along its orbit at a given time, relative to its parent (km, parent-centred — a moon's position is relative to its planet, not the star; the caller composes these up the parent chain for an absolute position — see resolveAbsolutePosition).
Standard Keplerian propagation: mean anomaly at time t -> eccentric anomaly (solveEccentricAnomaly) -> true anomaly + radius -> position in the orbital (perifocal) plane -> rotated into the reference frame by the three orientation angles (inclination, ascending node, argument of periapsis) and, when set, out of the elements' own reference plane (see OrbitalElements.referencePlanePole). This is the same transform any orbital mechanics reference (e.g. Vallado's "Fundamentals of Astrodynamics") gives for classical-element propagation — not specific to any one body.