Spacecraft planetary capture using gravity assist manoeuvres

M. Macdonald, C.R. McInnes

Research output: Contribution to journalArticle

25 Citations (Scopus)
159 Downloads (Pure)

Abstract

If the arrival speed at a target body can be increased from the very low hyperbolic excesses required to perform a low-thrust capture maneuver, then potentially significant savings can be made in the heliocentric mission duration if a bound orbit about the target planet can be maintained. We define a bound orbit as having an apoapsis that is positive but less than infinity; however, because this is not a practical limit and is instead a theoretical limit we examine the impact of reducing the target apoapsis to more realistic and useful values within specific case studies. Furthermore, an increase in arrival velocity can be expected to yield a benefit in mission launch mass.
Original languageEnglish
Pages (from-to)365-369
Number of pages4
JournalJournal of Guidance, Control and Dynamics
Volume28
Issue number2
Publication statusPublished - 2005

Fingerprint

Interplanetary spacecraft
interplanetary spacecraft
maneuvers
Spacecraft
savings
Gravity
Gravitation
Orbits
spacecraft
planet
thrust
gravity
gravitation
Target
arrivals
Planets
Orbit
low thrust
orbits
infinity

Keywords

  • spacecraft
  • planets
  • space travel
  • guidance systems
  • gravity

Cite this

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Spacecraft planetary capture using gravity assist manoeuvres. / Macdonald, M.; McInnes, C.R.

In: Journal of Guidance, Control and Dynamics, Vol. 28, No. 2, 2005, p. 365-369.

Research output: Contribution to journalArticle

TY - JOUR

T1 - Spacecraft planetary capture using gravity assist manoeuvres

AU - Macdonald, M.

AU - McInnes, C.R.

PY - 2005

Y1 - 2005

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AB - If the arrival speed at a target body can be increased from the very low hyperbolic excesses required to perform a low-thrust capture maneuver, then potentially significant savings can be made in the heliocentric mission duration if a bound orbit about the target planet can be maintained. We define a bound orbit as having an apoapsis that is positive but less than infinity; however, because this is not a practical limit and is instead a theoretical limit we examine the impact of reducing the target apoapsis to more realistic and useful values within specific case studies. Furthermore, an increase in arrival velocity can be expected to yield a benefit in mission launch mass.

KW - spacecraft

KW - planets

KW - space travel

KW - guidance systems

KW - gravity

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M3 - Article

VL - 28

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JO - Journal of Guidance, Control and Dynamics

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