Sun Perturbation - RAAN

vCalc Reviewed
Equation / Last modified by Administrator on 2015/06/09 07:11
`dotOmega_"Sun" = `
Rating
ID
vCalc.Sun Perturbation - RAAN
UUID
f37f8f5e-ed20-11e3-b7aa-bc764e2038f2

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 (`dotOmega`) 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).

 

SunPerturbationRAAN-illustration.png

Notes

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