Hybrid low-thrust transfers to eight-shaped orbits for polar observation

Jeannette Heiligers, Matteo Ceriotti, Colin McInnes

Research output: Contribution to conferencePaper

2 Citations (Scopus)

Abstract

In this paper, transfers from low Earth orbit (LEO) to so-called eight-shaped orbits at the collinear libration points in the circular restricted three-body problem are investigated. The potential of these orbits (both natural and sail
displaced) for high-latitude observation and telecommunication has recently been established. The transfer is modelled by distinguishing between a near-Earth phase and an interplanetary phase. The near-Earth phase is first
assumed to be executed with the Soyuz Fregat upper-stage, which brings the spacecraft from LEO to a highly elliptic orbit. From there, the interplanetary phase is initiated which uses low-thrust propulsion to inject the spacecraft into
one of the eight-shaped orbit’s manifolds. Both solar electric propulsion (SEP), solar sailing and hybridised SEP and solar sailing are considered for this phase. The objective is to maximise the mass delivered to the eight-shaped orbit
starting from a realistic Soyuz launch vehicle performance into LEO. Optimal trajectories are obtained by solving the optimal control problem in the interplanetary phase with a direct pseudospectral method. The results show that (over the full range of propulsion techniques) 1564 to 1603 kg can be injected into a natural eight-shaped orbit. Within this relatively small range, hybrid propulsion performs best in terms of mass delivered to the eight-shaped orbit, while SEP enables the fastest transfer times. With the interplanetary phase optimised, the upper-stage near-Earth phase is replaced by a multi-revolution low-thrust spiral. Locally optimal control laws for the SEP thruster and solar sail are derived to minimise the time of flight in the spiral. Both pure SEP and hybrid spiral show a significant reduction in the mass required in LEO to deliver the spacecraft to the eight-shaped orbits. While hybrid propulsion did not stand
out for the use of an upper-stage near-Earth phase, it does for the use of a low-thrust spiral as it significantly reduces the spiral time with respect to the pure SEP case.
LanguageEnglish
PagesIAC-12-C1.4.2
Number of pages19
Publication statusPublished - 1 Oct 2012
Event63rd International Astronautical Congress - Naples, Italy
Duration: 1 Oct 20125 Oct 2012

Conference

Conference63rd International Astronautical Congress
CountryItaly
CityNaples
Period1/10/125/10/12

Fingerprint

Orbits
Electric propulsion
Earth (planet)
Propulsion
Spacecraft
Vehicle performance
Launch vehicles
Telecommunication
Trajectories

Keywords

  • low-thrust propulsion
  • three body problem
  • interplanetary trajectory design
  • solar electric propulsion (SEP)
  • eight-shaped orbits
  • polar observation

Cite this

Heiligers, J., Ceriotti, M., & McInnes, C. (2012). Hybrid low-thrust transfers to eight-shaped orbits for polar observation. IAC-12-C1.4.2. Paper presented at 63rd International Astronautical Congress, Naples, Italy.
Heiligers, Jeannette ; Ceriotti, Matteo ; McInnes, Colin. / Hybrid low-thrust transfers to eight-shaped orbits for polar observation. Paper presented at 63rd International Astronautical Congress, Naples, Italy.19 p.
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Heiligers, J, Ceriotti, M & McInnes, C 2012, 'Hybrid low-thrust transfers to eight-shaped orbits for polar observation' Paper presented at 63rd International Astronautical Congress, Naples, Italy, 1/10/12 - 5/10/12, pp. IAC-12-C1.4.2.

Hybrid low-thrust transfers to eight-shaped orbits for polar observation. / Heiligers, Jeannette; Ceriotti, Matteo; McInnes, Colin.

2012. IAC-12-C1.4.2 Paper presented at 63rd International Astronautical Congress, Naples, Italy.

Research output: Contribution to conferencePaper

TY - CONF

T1 - Hybrid low-thrust transfers to eight-shaped orbits for polar observation

AU - Heiligers, Jeannette

AU - Ceriotti, Matteo

AU - McInnes, Colin

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N2 - In this paper, transfers from low Earth orbit (LEO) to so-called eight-shaped orbits at the collinear libration points in the circular restricted three-body problem are investigated. The potential of these orbits (both natural and sail displaced) for high-latitude observation and telecommunication has recently been established. The transfer is modelled by distinguishing between a near-Earth phase and an interplanetary phase. The near-Earth phase is first assumed to be executed with the Soyuz Fregat upper-stage, which brings the spacecraft from LEO to a highly elliptic orbit. From there, the interplanetary phase is initiated which uses low-thrust propulsion to inject the spacecraft into one of the eight-shaped orbit’s manifolds. Both solar electric propulsion (SEP), solar sailing and hybridised SEP and solar sailing are considered for this phase. The objective is to maximise the mass delivered to the eight-shaped orbit starting from a realistic Soyuz launch vehicle performance into LEO. Optimal trajectories are obtained by solving the optimal control problem in the interplanetary phase with a direct pseudospectral method. The results show that (over the full range of propulsion techniques) 1564 to 1603 kg can be injected into a natural eight-shaped orbit. Within this relatively small range, hybrid propulsion performs best in terms of mass delivered to the eight-shaped orbit, while SEP enables the fastest transfer times. With the interplanetary phase optimised, the upper-stage near-Earth phase is replaced by a multi-revolution low-thrust spiral. Locally optimal control laws for the SEP thruster and solar sail are derived to minimise the time of flight in the spiral. Both pure SEP and hybrid spiral show a significant reduction in the mass required in LEO to deliver the spacecraft to the eight-shaped orbits. While hybrid propulsion did not stand out for the use of an upper-stage near-Earth phase, it does for the use of a low-thrust spiral as it significantly reduces the spiral time with respect to the pure SEP case.

AB - In this paper, transfers from low Earth orbit (LEO) to so-called eight-shaped orbits at the collinear libration points in the circular restricted three-body problem are investigated. The potential of these orbits (both natural and sail displaced) for high-latitude observation and telecommunication has recently been established. The transfer is modelled by distinguishing between a near-Earth phase and an interplanetary phase. The near-Earth phase is first assumed to be executed with the Soyuz Fregat upper-stage, which brings the spacecraft from LEO to a highly elliptic orbit. From there, the interplanetary phase is initiated which uses low-thrust propulsion to inject the spacecraft into one of the eight-shaped orbit’s manifolds. Both solar electric propulsion (SEP), solar sailing and hybridised SEP and solar sailing are considered for this phase. The objective is to maximise the mass delivered to the eight-shaped orbit starting from a realistic Soyuz launch vehicle performance into LEO. Optimal trajectories are obtained by solving the optimal control problem in the interplanetary phase with a direct pseudospectral method. The results show that (over the full range of propulsion techniques) 1564 to 1603 kg can be injected into a natural eight-shaped orbit. Within this relatively small range, hybrid propulsion performs best in terms of mass delivered to the eight-shaped orbit, while SEP enables the fastest transfer times. With the interplanetary phase optimised, the upper-stage near-Earth phase is replaced by a multi-revolution low-thrust spiral. Locally optimal control laws for the SEP thruster and solar sail are derived to minimise the time of flight in the spiral. Both pure SEP and hybrid spiral show a significant reduction in the mass required in LEO to deliver the spacecraft to the eight-shaped orbits. While hybrid propulsion did not stand out for the use of an upper-stage near-Earth phase, it does for the use of a low-thrust spiral as it significantly reduces the spiral time with respect to the pure SEP case.

KW - low-thrust propulsion

KW - three body problem

KW - interplanetary trajectory design

KW - solar electric propulsion (SEP)

KW - eight-shaped orbits

KW - polar observation

UR - http://www.iac2012.org/

M3 - Paper

SP - IAC-12-C1.4.2

ER -

Heiligers J, Ceriotti M, McInnes C. Hybrid low-thrust transfers to eight-shaped orbits for polar observation. 2012. Paper presented at 63rd International Astronautical Congress, Naples, Italy.