Transfer strategies to the L3 libration point of the Sun-Earth system

Title

Transfer strategies to the L3 libration point of the Sun-Earth system

 Author

Tantardini, M.T.

Contributor

Noomen, R. (mentor)
Ambrosius, B.A.C. (mentor)

Faculty

Aerospace Engineering

 Department

SpE/ AS

 Date

2009-11-20

 Abstract

In this contribution, we investigate several trajectory design methods to transfer a spacecraft to the L3 point of the Sun-Earth Circular Restricted 3-Body Problem (CR3BP). Such a study aims at performing an investigation into an area that is so far little explored: the vicinity of L3 has never been the destination of a space mission, and in literature there is a big gap about transfers to the Sun-Earth L3 libration point. We consider several strategies and design methods: various types of two-burn impulsive trajectories in a Sun-spacecraft two-body model, a low-thrust transfer, an approach based on travelling on invariant manifolds of periodic orbits in the Sun-Earth CR3BP, and finally a patched conics strategy exploiting the gravity assist of the nearby planets. We discuss advantages and drawbacks, and we estimate propellant budget and time of flight requirements of each.

 Subject

trajectory design

 To reference this document use:

http://resolver.tudelft.nl/uuid:df72fe33-57f0-43ec-aab1-0baafd119513

 Embargo date

2009-12-08

 Part of collection

Student theses

 Document type

master thesis

 Rights

(c) 2009 Tantardini, M.T.
Files
PDF Tantardini_M_-_final_thesis.pdf 7.33 MB
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