The algorithm of the two-impulse time-fixed noncoplanar rendezvous with drag and oblateness effects

The algorithm that generates the exact solution of the two-impulse noncopla nar rendezvous in general elliptic orbit is presented. The motion of the ma neuvering spacecraft is referred to a rotating reference frame attached to the passive spacecraft and dragging and precessing at the same rate as that spacecraft. An iterative scheme is devised to find the magnitude and orien tation of the initiating impulse that brings the active spacecraft to a des ired target point in the vicinity of the passive spacecraft in a given time . When the rendezvous point is the vicinity of the passive spacecraft and n ot at the passive vehicle location itself, the linear distance between the two vehicles will exhibit variations along their post-rendezvous common orb it which can be of the order of kilometers for highly eccentric orbits. The se natural oscillations can be minimized by targeting the active vehicle to the immediate proximity of the passive spacecraft and be totally eliminate d by targeting to the passive vehicle location itself.