Optimal solar sail interplanetary heteroclinic transfers for novel space applications

Giorgio Mingotti, Jeannette Heiligers, Colin McInnes

Research output: Contribution to conferencePaper

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Abstract

This paper investigates the design and optimization of solar sail interplanetary trajectories connecting both Libration Point Orbits (LPOs) and Distant Periodic Orbits (DPOs) belonging to different restricted three-body problems: namely the Sun-Earth model and the Sun-Venus one. Assuming the Sun always as first primary, the Earth and Venus are the second primary, and their relative models are coupled together with the view of defining heteroclinic connections. On suitable Poincare sections, solar sail sets are constructed to obtain transit conditions from LPOs of the departure dynamical system to either LPOs or DPOs of the arrival one. Starting from initial guesses that assume a constant attitude of the solar sail, an optimal control problem is formulated, encompassing a trade-off between minimum transfer time and minimum solar sail steering effort, and it is solved with a direct pseudospectral method. At the optimization stage, variable attitude solar sails are investigated, assuming spacecraft with different control capabilities.
Original languageEnglish
Number of pages37
Publication statusPublished - 4 Aug 2014
EventAIAA/AAS Astrodynamics Specialist Conference 2014 - California, San Diego, United States
Duration: 4 Aug 20147 Aug 2014

Conference

ConferenceAIAA/AAS Astrodynamics Specialist Conference 2014
CountryUnited States
CitySan Diego
Period4/08/147/08/14

Fingerprint

Space applications
Orbits
Sun
Solar sails
Earth (planet)
Spacecraft
Dynamical systems
Trajectories

Keywords

  • sunjammer
  • solar sailing
  • trajectory optimisation
  • heteroclinic connections
  • circular restricted three-body problem
  • libration point orbits

Cite this

Mingotti, G., Heiligers, J., & McInnes, C. (2014). Optimal solar sail interplanetary heteroclinic transfers for novel space applications. Paper presented at AIAA/AAS Astrodynamics Specialist Conference 2014, San Diego, United States.
Mingotti, Giorgio ; Heiligers, Jeannette ; McInnes, Colin. / Optimal solar sail interplanetary heteroclinic transfers for novel space applications. Paper presented at AIAA/AAS Astrodynamics Specialist Conference 2014, San Diego, United States.37 p.
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abstract = "This paper investigates the design and optimization of solar sail interplanetary trajectories connecting both Libration Point Orbits (LPOs) and Distant Periodic Orbits (DPOs) belonging to different restricted three-body problems: namely the Sun-Earth model and the Sun-Venus one. Assuming the Sun always as first primary, the Earth and Venus are the second primary, and their relative models are coupled together with the view of defining heteroclinic connections. On suitable Poincare sections, solar sail sets are constructed to obtain transit conditions from LPOs of the departure dynamical system to either LPOs or DPOs of the arrival one. Starting from initial guesses that assume a constant attitude of the solar sail, an optimal control problem is formulated, encompassing a trade-off between minimum transfer time and minimum solar sail steering effort, and it is solved with a direct pseudospectral method. At the optimization stage, variable attitude solar sails are investigated, assuming spacecraft with different control capabilities.",
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Mingotti, G, Heiligers, J & McInnes, C 2014, 'Optimal solar sail interplanetary heteroclinic transfers for novel space applications' Paper presented at AIAA/AAS Astrodynamics Specialist Conference 2014, San Diego, United States, 4/08/14 - 7/08/14, .

Optimal solar sail interplanetary heteroclinic transfers for novel space applications. / Mingotti, Giorgio; Heiligers, Jeannette; McInnes, Colin.

2014. Paper presented at AIAA/AAS Astrodynamics Specialist Conference 2014, San Diego, United States.

Research output: Contribution to conferencePaper

TY - CONF

T1 - Optimal solar sail interplanetary heteroclinic transfers for novel space applications

AU - Mingotti, Giorgio

AU - Heiligers, Jeannette

AU - McInnes, Colin

PY - 2014/8/4

Y1 - 2014/8/4

N2 - This paper investigates the design and optimization of solar sail interplanetary trajectories connecting both Libration Point Orbits (LPOs) and Distant Periodic Orbits (DPOs) belonging to different restricted three-body problems: namely the Sun-Earth model and the Sun-Venus one. Assuming the Sun always as first primary, the Earth and Venus are the second primary, and their relative models are coupled together with the view of defining heteroclinic connections. On suitable Poincare sections, solar sail sets are constructed to obtain transit conditions from LPOs of the departure dynamical system to either LPOs or DPOs of the arrival one. Starting from initial guesses that assume a constant attitude of the solar sail, an optimal control problem is formulated, encompassing a trade-off between minimum transfer time and minimum solar sail steering effort, and it is solved with a direct pseudospectral method. At the optimization stage, variable attitude solar sails are investigated, assuming spacecraft with different control capabilities.

AB - This paper investigates the design and optimization of solar sail interplanetary trajectories connecting both Libration Point Orbits (LPOs) and Distant Periodic Orbits (DPOs) belonging to different restricted three-body problems: namely the Sun-Earth model and the Sun-Venus one. Assuming the Sun always as first primary, the Earth and Venus are the second primary, and their relative models are coupled together with the view of defining heteroclinic connections. On suitable Poincare sections, solar sail sets are constructed to obtain transit conditions from LPOs of the departure dynamical system to either LPOs or DPOs of the arrival one. Starting from initial guesses that assume a constant attitude of the solar sail, an optimal control problem is formulated, encompassing a trade-off between minimum transfer time and minimum solar sail steering effort, and it is solved with a direct pseudospectral method. At the optimization stage, variable attitude solar sails are investigated, assuming spacecraft with different control capabilities.

KW - sunjammer

KW - solar sailing

KW - trajectory optimisation

KW - heteroclinic connections

KW - circular restricted three-body problem

KW - libration point orbits

UR - http://www.space-flight.org/docs/2014_astro/2014_astro.html

M3 - Paper

ER -

Mingotti G, Heiligers J, McInnes C. Optimal solar sail interplanetary heteroclinic transfers for novel space applications. 2014. Paper presented at AIAA/AAS Astrodynamics Specialist Conference 2014, San Diego, United States.