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Astrodynamics 2020, 4(3): 193-204 https://doi.org/10.1007/s42064-019-0057-x
Research Article | Issue | Published: 02 August 2019

Optimal solar sail transfers to circular Earth-synchronous displaced orbits

Show Author's Information Alessandro A. Quarta( ),  Giovanni Mengali,  Marco Bassetto
Department of Civil and Industrial Engineering, University of Pisa, Pisa I-56122, Italy
Keywords:
trajectory optimization, solar sail, synchronous displaced orbit
Cite this article:
Quarta AA, Mengali G, Bassetto M. Optimal solar sail transfers to circular Earth-synchronous displaced orbits. Astrodynamics, 2020, 4(3): 193-204. https://doi.org/10.1007/s42064-019-0057-x
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Abstract Full text About this article

The aim of this paper is to evaluate the minimum flight time of a solar sail-based spacecraft towards Earth-synchronous (heliocentric) circular displaced orbits. These are special displaced non-Keplerian orbits characterized by a period of one year, which makes them suitable for the observation of Earth’s polar regions. The solar sail is modeled as a flat and purely reflective film with medium-low performance, that is, with a characteristic acceleration less than one millimeter per second squared. Starting from a circular parking orbit of radius equal to one astronomical unit, the optimal steering law is sought by considering the characteristic acceleration that is required for the maintenance of the target Earth-synchronous displaced orbit. The indirect approach used for the calculation of the optimal transfer trajectory allows the minimum flight time to be correlated with several Earth-synchronous displaced orbits, each one being characterized by given values of Earth-spacecraft distance and displacement over the ecliptic. The proposed mathematical model is validated by comparison with results available in the literature, in which a piecewise-constant steering law is used to find the optimal flight time for a transfer towards a one-year Type I non-Keplerian orbit.


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About this article

Optimal solar sail transfers to circular Earth-synchronous displaced orbits

Show Author's information Alessandro A. Quarta( ), Giovanni Mengali, Marco Bassetto
Department of Civil and Industrial Engineering, University of Pisa, Pisa I-56122, Italy

Abstract

The aim of this paper is to evaluate the minimum flight time of a solar sail-based spacecraft towards Earth-synchronous (heliocentric) circular displaced orbits. These are special displaced non-Keplerian orbits characterized by a period of one year, which makes them suitable for the observation of Earth’s polar regions. The solar sail is modeled as a flat and purely reflective film with medium-low performance, that is, with a characteristic acceleration less than one millimeter per second squared. Starting from a circular parking orbit of radius equal to one astronomical unit, the optimal steering law is sought by considering the characteristic acceleration that is required for the maintenance of the target Earth-synchronous displaced orbit. The indirect approach used for the calculation of the optimal transfer trajectory allows the minimum flight time to be correlated with several Earth-synchronous displaced orbits, each one being characterized by given values of Earth-spacecraft distance and displacement over the ecliptic. The proposed mathematical model is validated by comparison with results available in the literature, in which a piecewise-constant steering law is used to find the optimal flight time for a transfer towards a one-year Type I non-Keplerian orbit.

Keywords: trajectory optimization, solar sail, synchronous displaced orbit

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Publication history
Copyright
Acknowledgements

Publication history

Received: 16 February 2019
Accepted: 04 May 2019
Published: 02 August 2019
Issue date: September 2020

Copyright

© Tsinghua University Press 2019

Acknowledgements

This work is supported by the University of Pisa, Progetti di Ricerca di Ateneo (Grant No. PRA_2018_44).

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