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Related Experiment Videos

ExoMars alternative escape trajectories with Soyuz/Fregat.

Jesús Gil-Fernández1, Carlos Corral Van Damme, Mariella Graziano

  • 1GMV S.A., Isaac Newton 11, P.T.M. Tres Cantos, 28760 Madrid, Spain. jesusgil@gmv.es

Annals of the New York Academy of Sciences
|March 3, 2006
PubMed
Summary

Researchers explored novel trajectories for the ExoMars mission to increase orbiter mass. By using lunar swing-bys and the Sun

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Area of Science:

  • Planetary Science
  • Astrodynamics
  • Space Mission Design

Background:

  • The ExoMars mission aims to orbit Mars and land a rover to search for signs of life.
  • Initial feasibility studies revealed a very small mass margin for the orbiter in a direct transfer scenario using Soyuz/Fregat.
  • This constraint necessitates exploring alternative trajectory designs to accommodate higher orbiter masses.

Purpose of the Study:

  • To investigate alternative interplanetary trajectories for the ExoMars mission.
  • To enhance the mass margin for the orbiter by utilizing lunar swing-bys and the Sun's gravity gradient.
  • To identify feasible trajectory designs that meet mission requirements for Mars arrival.

Main Methods:

  • Utilized WESBOT, a GMV tool, for designing Weak Stability Boundary (WSB) transfers to the Moon and Earth escape trajectories.

Related Experiment Videos

  • Analyzed trajectories involving multiple lunar and Earth swing-bys, leveraging the Sun's gravity gradient for DeltaV savings.
  • Employed a systematic search for initial guess trajectories, combining patched conics and multiple shooting methods.
  • Optimized departure conditions (date and orbit) while maintaining the required Mars arrival date.

    • Main Results:

    • Identified and presented optimal trajectories with varying morphologies for different swing-by strategies.
    • Demonstrated the potential for significant mass gains through the strategic use of gravity assists.
    • The analysis confirmed the applicability of these novel trajectory designs to the ExoMars mission.

    Conclusions:

    • Combined lunar swing-bys and Sun gravity gradient maneuvers offer a viable solution for increasing orbiter mass on Mars transfer trajectories.
    • These advanced trajectory design techniques are crucial for overcoming mass limitations in interplanetary missions like ExoMars.
    • The study provides a foundation for future mission planning requiring enhanced payload capacity.