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

Defined in File frame_conversions.cc

Function Documentation¶

Vec6 lupnt::MoonPaToCi(Real t_tdb, const Vec6 &rv_pa)¶

Converts a state vector from MoonPa (Moon-fixed, principal-axis frame) to MoonCi (Moon-centered inertial, ICRF-aligned axes) at epoch t_tdb.

Used by ConvertFrame as the inverse of MoonCiToPa, e.g. to bring a gravity-model or surface-relative lunar state back into the inertial frame for dynamics propagation. Internally applies the transpose of RotMoonCiToPa (and its time derivative) to rotate both position and velocity.

Note

Astrodynamics Convention & Modeling Reference, Version 1.1, Page 42

Parameters:

t_tdb – Epoch [s, TDB since J2000]
rv_pa – Position+velocity in MoonPa (Moon-fixed principal axes) [m, m/s]

Returns:

Position+velocity in MoonCi [m, m/s]