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

• Defined in File frame_conversions.cc

Function Documentation

Vec6 lupnt::MoonCiToPa(Real t_tdb, const Vec6 &rv_mi)

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

Used by ConvertFrame to express lunar-orbiter/lander states in the body-fixed principal-axis frame — e.g. for lunar gravity-field evaluation, surface feature lookups, and as the bridge to MoonMe (via MoonPaToMe). Internally applies 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_mi – Position+velocity in MoonCi [m, m/s]

Returns:

Position+velocity in MoonPa (Moon-fixed principal axes) [m, m/s]