Function lupnt::MoonCiToGcrf(Real, const Vec6&)¶

Defined in File frame_conversions.cc

Function Documentation¶

Vec6 lupnt::MoonCiToGcrf(Real t_tdb, const Vec6 &rv_mi)¶

Converts a state vector from MoonCi (Moon-centered inertial) to GCRF (Earth-centered inertial), by adding the Earth-to-Moon position/velocity at t_tdb.

Used by ConvertFrame as the exit point from the Moon-centered frame family back to the GCRF hub frame.

Note

Astrodynamics Convention & Modeling Reference, Version 1.1, Page 40

Parameters:

t_tdb – Epoch [s, TDB since J2000]
rv_mi – Position+velocity in MoonCi (Moon-centered inertial) [m, m/s]

Returns:

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