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

Giorgio Mingotti, Francesco Topputo, Franco Bernelli-Zazzara

Research output: Contribution to journalArticle

49 Citations (Scopus)

Abstract

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.
LanguageEnglish
Pages169-188
JournalCelestial Mechanics and Dynamical Astronomy
Volume110
Issue number2
DOIs
Publication statusPublished - Jun 2011

Fingerprint

low thrust
Mars
Ballistics
Sun
mars
ballistics
escape
sun
thrust control
thrust
Earth (planet)
high impulse
Attainable Set
lunar orbits
flight time
specific impulse
N-body Problem
Eccentricity
Moon
Inclination

Keywords

  • restricted three-body problem
  • invariant manifolds
  • low-thrust transfers
  • n-body models
  • ballistic capture
  • lunar-gravity assist

Cite this

Mingotti, Giorgio ; Topputo, Francesco ; Bernelli-Zazzara, Franco. / Earth-Mars transfers with ballistic escape and low-thrust capture. In: Celestial Mechanics and Dynamical Astronomy. 2011 ; Vol. 110, No. 2. pp. 169-188.
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Earth-Mars transfers with ballistic escape and low-thrust capture. / Mingotti, Giorgio; Topputo, Francesco; Bernelli-Zazzara, Franco.

In: Celestial Mechanics and Dynamical Astronomy, Vol. 110, No. 2, 06.2011, p. 169-188.

Research output: Contribution to journalArticle

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