New State Transition Matrix for Formation Flying in J2-Perturbed Elliptic Orbits

摘要: A state transition matrix for formation flying in eccentric orbits is considered this paper. The relative motion of the obeys Tschauner–Hempel equations, which are extended presence a J2 perturbation. Furthermore, transitionmatrix equations J2, and it demonstrated that becomes solution equations. Because only uses osculating orbital elements initial does not use mean elements, an analytical treatment possible. When first-order term errors sometimes become large compared with distancemultiplied by time range longer thanone orbit period.Amethod to suppress numerically also proposed.