Function lupnt::RotMoonOpToCi

• Defined in File frame_conversions.cc

Function Documentation

Mat3 lupnt::RotMoonOpToCi(Real t_tdb)

Returns the MoonOp-to-MoonCi rotation matrix R_op2ci at epoch t_tdb, whose columns [x_OP, y_OP, z_OP] (expressed in MoonCi) define the “orbit plane” frame of Ely (2005): z_OP along the Earth-Moon orbital angular-momentum direction, x_OP the projection of the lunar mean-Earth pole onto the plane normal to z_OP, and y_OP completing the right-handed triad, such that v_CI = R_op2ci * v_OP.

Used internally by MoonOpToCi/MoonCiToOp (the latter via its transpose) to rotate position/velocity between the Moon-centered inertial frame and the frozen-orbit “orbit plane” frame.

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:

t_tdb – Epoch [s, TDB since J2000]

Returns:

3x3 MoonOp-to-MoonCi rotation matrix R_op2ci (dimensionless)