Luni-solar perturbations for mission design in highly elliptical orbits

This paper presents a method for designing perturbation-enhanced trajectory for reentry or graveyard disposal. The analysis of the manoeuvre in the phase space allows characterising the long-term evolution of the orbit under the effects of natural perturbations. Then, maps are produced to characterise the stability of several initial conditions in the phase space considering a more detailed model of the dynamics. In this case, single and averaged semi-analytical techniques are used for reducing the computational time, still guarantying a good accuracy. The method applicability is shown for the design of the end-of-life of INTEGRAL and XMM-Newton missions. Previous results in the framework of the study of these missions are here used to explain the general framework of the proposed method.

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