Sunjammer: Preliminary end-to-end mission design

Jeannette Heiligers, Benjamin Diedrich, Bill Derbes, Colin McInnes

Research output: Contribution to conferencePaper

Abstract

This paper provides a preliminary end-to-end mission design for NASA’s Sunjammer solar sail mission, which is scheduled for ground test deployment in 2015 with launch at a later date and targets the sub-L1 region for advanced solar storm warning. The artificial equilibrium points (AEPs) in the sub-L1 region accessible by the Sunjammer sail as well as solar sail Halo orbits are investigated. Subsequently, the fly-out from an Earth GTO into either a selected sub-L1 AEP or Halo orbit is optimized for a trade-off between the AV to be provided at GTO perigee and the time of flight. In addition, interesting, time-optimal extended mission scenarios are presented to underpin future solar sail mission applications, e.g. transferring to an AEP high above the ecliptic plane for high-latitude Earth observation. All analyses are carried out both for an ideal Sunjammer sail performance as well as for a realistic performance derived from a detailed sail structural analysis. A comparison of the results shows that non-ideal sail properties increase the time of flight of the trajectories by 2.4 - 7.9%.

Conference

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

Fingerprint

Orbits
Earth (planet)
Structural analysis
NASA
Trajectories

Keywords

  • sunjammer
  • soalr sailing
  • trajectory optimisation
  • space mission design
  • artificial equilibrium points
  • hao orbits
  • extended mission concepts
  • circular restricted three-body problem

Cite this

Heiligers, J., Diedrich, B., Derbes, B., & McInnes, C. (2014). Sunjammer: Preliminary end-to-end mission design. Paper presented at AIAA/AAS Astrodynamics Specialist Conference 2014, San Diego, United States.
Heiligers, Jeannette ; Diedrich, Benjamin ; Derbes, Bill ; McInnes, Colin. / Sunjammer : Preliminary end-to-end mission design. Paper presented at AIAA/AAS Astrodynamics Specialist Conference 2014, San Diego, United States.27 p.
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title = "Sunjammer: Preliminary end-to-end mission design",
abstract = "This paper provides a preliminary end-to-end mission design for NASA’s Sunjammer solar sail mission, which is scheduled for ground test deployment in 2015 with launch at a later date and targets the sub-L1 region for advanced solar storm warning. The artificial equilibrium points (AEPs) in the sub-L1 region accessible by the Sunjammer sail as well as solar sail Halo orbits are investigated. Subsequently, the fly-out from an Earth GTO into either a selected sub-L1 AEP or Halo orbit is optimized for a trade-off between the AV to be provided at GTO perigee and the time of flight. In addition, interesting, time-optimal extended mission scenarios are presented to underpin future solar sail mission applications, e.g. transferring to an AEP high above the ecliptic plane for high-latitude Earth observation. All analyses are carried out both for an ideal Sunjammer sail performance as well as for a realistic performance derived from a detailed sail structural analysis. A comparison of the results shows that non-ideal sail properties increase the time of flight of the trajectories by 2.4 - 7.9{\%}.",
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author = "Jeannette Heiligers and Benjamin Diedrich and Bill Derbes and Colin McInnes",
year = "2014",
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day = "4",
language = "English",
note = "AIAA/AAS Astrodynamics Specialist Conference 2014 ; Conference date: 04-08-2014 Through 07-08-2014",

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Heiligers, J, Diedrich, B, Derbes, B & McInnes, C 2014, 'Sunjammer: Preliminary end-to-end mission design' Paper presented at AIAA/AAS Astrodynamics Specialist Conference 2014, San Diego, United States, 4/08/14 - 7/08/14, .

Sunjammer : Preliminary end-to-end mission design. / Heiligers, Jeannette; Diedrich, Benjamin; Derbes, Bill; McInnes, Colin.

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

Research output: Contribution to conferencePaper

TY - CONF

T1 - Sunjammer

T2 - Preliminary end-to-end mission design

AU - Heiligers, Jeannette

AU - Diedrich, Benjamin

AU - Derbes, Bill

AU - McInnes, Colin

PY - 2014/8/4

Y1 - 2014/8/4

N2 - This paper provides a preliminary end-to-end mission design for NASA’s Sunjammer solar sail mission, which is scheduled for ground test deployment in 2015 with launch at a later date and targets the sub-L1 region for advanced solar storm warning. The artificial equilibrium points (AEPs) in the sub-L1 region accessible by the Sunjammer sail as well as solar sail Halo orbits are investigated. Subsequently, the fly-out from an Earth GTO into either a selected sub-L1 AEP or Halo orbit is optimized for a trade-off between the AV to be provided at GTO perigee and the time of flight. In addition, interesting, time-optimal extended mission scenarios are presented to underpin future solar sail mission applications, e.g. transferring to an AEP high above the ecliptic plane for high-latitude Earth observation. All analyses are carried out both for an ideal Sunjammer sail performance as well as for a realistic performance derived from a detailed sail structural analysis. A comparison of the results shows that non-ideal sail properties increase the time of flight of the trajectories by 2.4 - 7.9%.

AB - This paper provides a preliminary end-to-end mission design for NASA’s Sunjammer solar sail mission, which is scheduled for ground test deployment in 2015 with launch at a later date and targets the sub-L1 region for advanced solar storm warning. The artificial equilibrium points (AEPs) in the sub-L1 region accessible by the Sunjammer sail as well as solar sail Halo orbits are investigated. Subsequently, the fly-out from an Earth GTO into either a selected sub-L1 AEP or Halo orbit is optimized for a trade-off between the AV to be provided at GTO perigee and the time of flight. In addition, interesting, time-optimal extended mission scenarios are presented to underpin future solar sail mission applications, e.g. transferring to an AEP high above the ecliptic plane for high-latitude Earth observation. All analyses are carried out both for an ideal Sunjammer sail performance as well as for a realistic performance derived from a detailed sail structural analysis. A comparison of the results shows that non-ideal sail properties increase the time of flight of the trajectories by 2.4 - 7.9%.

KW - sunjammer

KW - soalr sailing

KW - trajectory optimisation

KW - space mission design

KW - artificial equilibrium points

KW - hao orbits

KW - extended mission concepts

KW - circular restricted three-body problem

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

M3 - Paper

ER -

Heiligers J, Diedrich B, Derbes B, McInnes C. Sunjammer: Preliminary end-to-end mission design. 2014. Paper presented at AIAA/AAS Astrodynamics Specialist Conference 2014, San Diego, United States.