Study on relative motion model of elliptical reference orbit under influence of J2 perturbation
AbstractThe most widely used relative motion model of satellite formation Flying is the Hill's equation and Clohessy-Wiltshire's (C.W's) equations. The linearized equations are based on three hypothesis: ideal sphere circular reference orbit and relative distance being close enough. The hypothesis brings model error that J2 Perturbation and elliptical reference Orbit isn't taken into accounted. A linearized relative motion model was addressed. Considering the impact of the J2 Perturbation on Secular drift of relative motion, mean orbit elements and instant orbit elements, relative motion model of elliptical reference orbit was developed based on initial instant orbit elements and its drift. Result of simulations demonstrates the efficacy of the model.