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

Defined in File frame_conversions.h

Function Documentation¶

Vec6 lupnt::MoonOpToCi(Real t_tdb, const Vec6 &rv_op)¶

Converts a state vector from MoonOp (Moon orbit-plane frame) to MoonCi (Moon-centered inertial) at epoch t_tdb.

Used by ConvertFrame as the inverse of MoonCiToOp, to bring a frozen-orbit “orbit plane” state back into the Moon-centered inertial frame for dynamics propagation. Internally applies RotMoonOpToCi.

Parameters:

t_tdb – Epoch [s, TDB since J2000]
rv_op – Position+velocity in MoonOp (Moon orbit-plane frame) [m, m/s]

Returns:

Position+velocity in MoonCi (Moon-centered inertial) [m, m/s]