I read about secondary effects which influence on orbit propagation like solar radiation, moon, etc. (https://en.wikipedia.org/wiki/Orbit_modeling). First I calculate position vector Rpqw to object (artificial satellite) using 6 orbit elements with following formulas:
u = v + ω r = a*(1-e*e)/(1+e*cos(v)) p = r * cos(v) q = r * sin(v) w = 0.0 RotationMatrix = R3(-Ω)R1(-i)R3(- ω) Rijk = RotationMatrix * Rpqw Where: U – latitude argument r – distance to object Rijk – coordinates of object in 3D space in ECI coordinate system (a.k.a. IJK - axis) a - semimajor axis i - inclination Ω - right ascension of the ascending node ω - argument of perigee v - true anomaly
I want to know when I must apply effects like solar radiation pressure or atmospheric drag and others, after I calculate Rijk or during the process? And does the applying order matter?