Function lupnt::GcrfToEme(const Vec6&)

Function Documentation

Vec6 lupnt::GcrfToEme(const Vec6 &rv_gcrf)

Converts a state vector from GCRF to EME2000 (J2000 mean equator/equinox) by applying the constant IAU frame-bias rotation.

EME2000 (a.k.a. ECI/J2000) is the conventional inertial frame used by many legacy ephemerides and dynamics models; ConvertFrame calls this when converting a GCRF state to/from Frame::EME/Frame::ECI. Unlike most other conversions in this header, the GCRF<->EME rotation is a fixed (time-independent) bias, so no epoch argument is needed.

Note

Astrodynamics Convention & Modeling Reference, Version 1.1, Page 39

Parameters:

rv_gcrf – Position+velocity in GCRF [m, m/s]

Returns:

Position+velocity in EME2000 (ECI) [m, m/s]