This equation computes the rate of change of the right ascension of the ascending node  (RAAN) of an orbit where the rate of change in deg/day results from the Moon's third-body gravitational influence on the orbit.  The inputs to this equation are the orbit inclination (i) and the number of orbit revolutions per day (n).

Notes

This computation is an approximation, as it neglects the perturbation caused by the change in orientation of the orbital plane relative to the Moon's orbital plane.