Optimal aeroassisted orbital rendezvous and interception

Optimal trajectories of aeroassisted orbital rendezvous and interception can be found when considering the general elliptic initial and target orbits. In this paper, both the minimum-fuel and minimum-time cases are taken into account so as to analyze the corresponding optimal results. Specifically, the initial state constraints at deorbit position and atmospheric entry have been re-derived firstly under the premise that the waiting time before the deorbit maneuver is taken as an optimization variable. Secondly, considering the limitation of factors such as heating-rate and load, the optimal trajectories of the aeroassisted orbital rendezvous with minimum-fuel and minimum-time are given. Besides, the profiles of relevant control variables are shown. Because the interception does not need terminal brake impulse strictly, the minimum-fuel aeroassisted interception problem under total time constraint is solved. The result indicates that the time constraints should be imposed prudently because they will increase three different kind of loads effected on chase vehicle. Finally, when under different maximum allowable distance of interception position situation, the optimal results of the minimum-time interception are conducted in detail.