Optimal maneuver strategy of flyaround orbit based on new relative orbit elements

摘要

This study investigates the representation and optimal maneuver strategy of the relative flyaround orbit. Based on the closed-form solution of linear approximated equations of relative motion, a new set of relative orbit elements are presented, instead of the relative position and velocity components, to describe intuitively the size, location, and orientation of the relative trajectory of the chaser with respect to the target, as well as the location of the chaser along its relative trajectory. Based on the new relative orbit elements, an optimal maneuver strategy of using one single instantaneous velocity impulse is presented, and the least cost solution of maneuvering from the coplanar flyaround orbit to the non-coplanar one is derived. Finally, the numerical simulation for the three-dimensional observation of space target is provided to verify the validation of optimal maneuver strategy.