Optimal low-thrust trajectories to earth-moon L2 halo orbits (circular problem)

Thomas F. Starchville, Robert Graham Melton

Research output: Contribution to journalArticle

14 Citations (Scopus)

Abstract

Development of optimal low-thrust transfer trajectories required between Earth and an Earth-Moon L2 halo orbit is examined. A general optimal solution method is constructed using sequential nonlinear programming to find minimum-propellant spacecraft transfers. Only a single thrust phase of the trajectory (using tangential steering) is optimized with the spacecraft traveling the remaining time on the stable manifold of the halo insertion point. The solution method is demonstrated for a number of insertion points on two different reference halos for the circular restricted three-body problem.

Original languageEnglish (US)
Pages (from-to)1741-1756
Number of pages16
JournalAdvances in the Astronautical Sciences
Volume97 PART 2
StatePublished - 1997

Fingerprint

low thrust
circular orbits
Moon
natural satellites
Spacecraft
halos
Orbits
spacecraft
thrust
Earth (planet)
trajectory
Trajectories
trajectories
insertion
Nonlinear programming
Propellants
nonlinear programming
three body problem
propellants
moon

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

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abstract = "Development of optimal low-thrust transfer trajectories required between Earth and an Earth-Moon L2 halo orbit is examined. A general optimal solution method is constructed using sequential nonlinear programming to find minimum-propellant spacecraft transfers. Only a single thrust phase of the trajectory (using tangential steering) is optimized with the spacecraft traveling the remaining time on the stable manifold of the halo insertion point. The solution method is demonstrated for a number of insertion points on two different reference halos for the circular restricted three-body problem.",
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Optimal low-thrust trajectories to earth-moon L2 halo orbits (circular problem). / Starchville, Thomas F.; Melton, Robert Graham.

In: Advances in the Astronautical Sciences, Vol. 97 PART 2, 1997, p. 1741-1756.

Research output: Contribution to journalArticle

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AU - Melton, Robert Graham

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AB - Development of optimal low-thrust transfer trajectories required between Earth and an Earth-Moon L2 halo orbit is examined. A general optimal solution method is constructed using sequential nonlinear programming to find minimum-propellant spacecraft transfers. Only a single thrust phase of the trajectory (using tangential steering) is optimized with the spacecraft traveling the remaining time on the stable manifold of the halo insertion point. The solution method is demonstrated for a number of insertion points on two different reference halos for the circular restricted three-body problem.

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