Advanced methods of low cost mission design for the Galilean moons exploration

The implementation of the deep space expeditions to the outer Solar system is the one of main priorities of modern astrodynamics One of the irritating factors for this is the probability of the life determination in the underground ocean at the Jovian icy moon Europa. In that regard the realization of the cosmic projects using the spacecraft - orbiters around the Jovian Galilean Moons and especially the descent modules implementation on their surface is one of the basic focuses of the current international cosmic space researches collaboration. The mission design of such cosmic projects must be executed using new advanced methods for their planning: Low Energy Tours exploring, Favourable Total Radiation Doze of the spacecraft (SC) provision, and tolerable maintenance of the SC's Time of Flight during the Jupiter system phase. Furthermore, the saving character of the trajectory design for the artificial satellite of the Galilean moon necessary required the smallness of the SC's velocity relative this moon, i.e. the smallness of the SC's hyperbolic velocity excess vector. In this work multibody bunch adaptive synthesis algorithms to overcome ballistic determinism expressed by existing of the integral of Jacobi in the basic CR3BP (circular restricted three body problem) are developed. It is shown that the diversity of the gravity of the ensemble in the Jovian system, not only complicates the accurate ballistic mission analysis, but, when its multibody effective use, allowing you to tailor flowed algorithms for the constructing scenarios of gravity assist maneuvers for interplanetary missions design, including circumvention of dangerous radiation areas, as well as landing at selected Galilean moon at a reasonable cost, resources and time.