Analytical three-phase transfer to a solar polar orbit using solar sail propulsion

Research output: Contribution to conferencePaper

1 Citation (Scopus)

Abstract

A general solution for a 3-phase transfer trajectory from the Earth to a solar polar orbit using solar sail propulsion is presented, deriving for the first time the optimal trajectory architecture without the need for engineering assumptions and numerical analysis. The 3-phase transfer presented involves spiralling in close to the Sun, performing a rapid inclination increase, and spiralling back out to the final target orbit. The general perturbation solution allows the split of inclination change per phase to be optimised for the minimum transfer duration, negating the need for assumptions used in previous numerical optimisations. This method offers significant advantages over the numerically optimised solutions currently available as it allows for a complete understanding of the optimal
structure of the trajectory to be gained. These results show that the 3-phase transfer can offer time savings of approximately 30% when compared with a 2-phase transfer. By further sub-dividing the spiral phases into shorter sections it is found that it is possible to further optimise the trajectory; this approach could theoretically be extended to approximate an optimal transfer trajectory. The simplest of these extensions, the 5-phase transfer, is found to offer only a 1% time saving compared with the 3-phase transfer, suggesting that further optimisation beyond the 3-phase transfer may yield only minor improvements. Comparison with existing numerical solutions shows the general perturbation solution to offer a 10% reduction in transfer time due to the optimisation of the amount of inclination change per phase. Thus, this analytical description of the time-optimal transfer trajectories for a mission to a solar polar orbit offers significant advantages for system design trade studies and future mission design.
LanguageEnglish
PagesIAC-14-C.6.11
Number of pages7
Publication statusPublished - 3 Oct 2014
Event65th International Astronautical Congress (IAC 2014) - Metro Toronto Convention Centre, Toronto, Canada
Duration: 29 Sep 20143 Oct 2014

Conference

Conference65th International Astronautical Congress (IAC 2014)
CountryCanada
CityToronto
Period29/09/143/10/14

Fingerprint

ice ridge
Propulsion
Orbits
trajectory
Trajectories
perturbation
Sun
Numerical analysis
savings
Earth (planet)
Systems analysis
engineering

Keywords

  • three-phase transfer
  • solar polar orbit
  • solar sailing
  • transfer trajectories
  • mission design

Cite this

McGrath, C., & Macdonald, M. (2014). Analytical three-phase transfer to a solar polar orbit using solar sail propulsion. IAC-14-C.6.11. Paper presented at 65th International Astronautical Congress (IAC 2014), Toronto, Canada.
McGrath, Ciara ; Macdonald, Malcolm. / Analytical three-phase transfer to a solar polar orbit using solar sail propulsion. Paper presented at 65th International Astronautical Congress (IAC 2014), Toronto, Canada.7 p.
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McGrath, C & Macdonald, M 2014, 'Analytical three-phase transfer to a solar polar orbit using solar sail propulsion' Paper presented at 65th International Astronautical Congress (IAC 2014), Toronto, Canada, 29/09/14 - 3/10/14, pp. IAC-14-C.6.11.

Analytical three-phase transfer to a solar polar orbit using solar sail propulsion. / McGrath, Ciara; Macdonald, Malcolm.

2014. IAC-14-C.6.11 Paper presented at 65th International Astronautical Congress (IAC 2014), Toronto, Canada.

Research output: Contribution to conferencePaper

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T1 - Analytical three-phase transfer to a solar polar orbit using solar sail propulsion

AU - McGrath, Ciara

AU - Macdonald, Malcolm

PY - 2014/10/3

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N2 - A general solution for a 3-phase transfer trajectory from the Earth to a solar polar orbit using solar sail propulsion is presented, deriving for the first time the optimal trajectory architecture without the need for engineering assumptions and numerical analysis. The 3-phase transfer presented involves spiralling in close to the Sun, performing a rapid inclination increase, and spiralling back out to the final target orbit. The general perturbation solution allows the split of inclination change per phase to be optimised for the minimum transfer duration, negating the need for assumptions used in previous numerical optimisations. This method offers significant advantages over the numerically optimised solutions currently available as it allows for a complete understanding of the optimalstructure of the trajectory to be gained. These results show that the 3-phase transfer can offer time savings of approximately 30% when compared with a 2-phase transfer. By further sub-dividing the spiral phases into shorter sections it is found that it is possible to further optimise the trajectory; this approach could theoretically be extended to approximate an optimal transfer trajectory. The simplest of these extensions, the 5-phase transfer, is found to offer only a 1% time saving compared with the 3-phase transfer, suggesting that further optimisation beyond the 3-phase transfer may yield only minor improvements. Comparison with existing numerical solutions shows the general perturbation solution to offer a 10% reduction in transfer time due to the optimisation of the amount of inclination change per phase. Thus, this analytical description of the time-optimal transfer trajectories for a mission to a solar polar orbit offers significant advantages for system design trade studies and future mission design.

AB - A general solution for a 3-phase transfer trajectory from the Earth to a solar polar orbit using solar sail propulsion is presented, deriving for the first time the optimal trajectory architecture without the need for engineering assumptions and numerical analysis. The 3-phase transfer presented involves spiralling in close to the Sun, performing a rapid inclination increase, and spiralling back out to the final target orbit. The general perturbation solution allows the split of inclination change per phase to be optimised for the minimum transfer duration, negating the need for assumptions used in previous numerical optimisations. This method offers significant advantages over the numerically optimised solutions currently available as it allows for a complete understanding of the optimalstructure of the trajectory to be gained. These results show that the 3-phase transfer can offer time savings of approximately 30% when compared with a 2-phase transfer. By further sub-dividing the spiral phases into shorter sections it is found that it is possible to further optimise the trajectory; this approach could theoretically be extended to approximate an optimal transfer trajectory. The simplest of these extensions, the 5-phase transfer, is found to offer only a 1% time saving compared with the 3-phase transfer, suggesting that further optimisation beyond the 3-phase transfer may yield only minor improvements. Comparison with existing numerical solutions shows the general perturbation solution to offer a 10% reduction in transfer time due to the optimisation of the amount of inclination change per phase. Thus, this analytical description of the time-optimal transfer trajectories for a mission to a solar polar orbit offers significant advantages for system design trade studies and future mission design.

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McGrath C, Macdonald M. Analytical three-phase transfer to a solar polar orbit using solar sail propulsion. 2014. Paper presented at 65th International Astronautical Congress (IAC 2014), Toronto, Canada.