Optimal satellite formation reconfiguration strategy based on relative orbital elements

This paper presents an analytical fuel-optimal impulsive formation reconfiguration strategy in terms of relative orbital elements (especially using the geometrically intuitive form called relative eccentricity and inclination vectors [E/I vectors]). The relative motion and orbit transfer problem is reparameterized in the form of relative orbit elements. Given a set of transfer conditions, the optimal impulsive strategy for a single satellite maneuver is formulated. Based on the analytical solution of a single satellite transfer, the proposed method is further extended to reconfiguration maneuvers for satellites flying in formation, which accounts for the optimization that relates to the satellites reassignment problem in the reconfiguration stage. Simulations are conducted to demonstrate the validity of the proposed approaches for both single satellite and formation flying reconfiguration scenarios.

► Optimal relative orbit maneuver is solved with a geometrical proof.
► Optimal impulses for formation reconfiguration are derived analytically.
► Analytical solutions are convenient for mission analysis or on-board application.