Research on optimum evading strategy from collision for spacecraft

This paper analyzes the colliding conditions for two orbital objects with different orbital planes. Using secular perturbations of SGP4/SDP4 propagator the time difference the two objects passing the intersection and the corresponding altitude difference can be computed. And after obtaining collision warning information the iteration method of finding optimum velocity increment is given for evading on the basis of orbital adjust. Then considering simplified perturbations the relations between the velocity increment in-track and the passing time difference is discussed which can provide the basic efficiency of the maneuver strategy.