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

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.

Note

T. A. Ely, ‘Stable Constellations of Frozen Elliptical Inclined Lunar Orbits’, J of Astronaut Sci, vol. 53, no. 3, pp. 301–316, Sep. 2005, doi: 10.1007/BF03546355.

Parameters:

  • rv_op –

  • t_tdb – Epoch [s, TDB since J2000]

  • rv_op – Position+velocity in MoonOp (Moon orbit-plane frame) [m, m/s]

Returns:

Vec6

Returns:

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