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

• Defined in File frame_conversions.cc

Function Documentation

Vec6 lupnt::EmrToGcrf(Real t_tdb, const Vec6 &rv_emr)

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

Used by ConvertFrame as the inverse of GcrfToEmr, to bring an Earth-Moon-rotating-frame state (e.g. a target point defined in EMR) back into the GCRF hub frame for dynamics propagation.

Note

Astrodynamics Convention & Modeling Reference, Version 1.1, Page 48

Parameters:

• t_tdb – Epoch [s, TDB since J2000]

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

Returns:

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