Earth-Mars transfers with ballistic escape and low-thrust capture

Details Earth-Mars transfers with ballistic escape and low-thrust capture Earth-Mars transfers with ballistic escape and low-thrust capture

Jun 2011

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2011cemda.110..169m&link_type=abstract

Celestial Mechanics and Dynamical Astronomy, Volume 110, Issue 2, pp.169-188

Astronomy and Astrophysics

Astronomy

1

Scientific paper

In this paper novel Earth-Mars transfers are presented. These transfers exploit the natural dynamics of n-body models as well as the high specific impulse typical of low-thrust systems. The Moon-perturbed version of the Sun-Earth problem is introduced to design ballistic escape orbits performing lunar gravity assists. The ballistic capture is designed in the Sun-Mars system where special attainable sets are defined and used to handle the low-thrust control. The complete trajectory is optimized in the full n-body problem which takes into account planets' orbital inclinations and eccentricities. Accurate, efficient solutions with reasonable flight times are presented and compared with known results.

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