Function lupnt::GcrfToEmr(Real, const Vec6&)

• Defined in File frame_conversions.cc

Function Documentation

Vec6 lupnt::GcrfToEmr(Real t_tdb, const Vec6 &rv_gcrf)

Converts a state vector from GCRF (Earth-centered inertial) to EMR (Earth-Moon Rotating frame), via InertialToSynodic relative to the instantaneous Earth-Moon-barycenter direction.

Used by ConvertFrame to express an Earth-centered inertial state in the rotating Earth-Moon frame — e.g. for visualizing/analyzing libration-point trajectories or cislunar transfer geometry relative to the Earth-Moon line.

Note

Astrodynamics Convention & Modeling Reference, Version 1.1, Page 48

Parameters:

• t_tdb – Epoch [s, TDB since J2000]

• rv_gcrf – Position+velocity in GCRF (Earth-centered inertial) [m, m/s]

Returns:

Position+velocity in EMR (Earth-Moon Rotating frame) [m, m/s]