Abstract

Within the context of both manned and robotic spaceflight activities, orbits near the Earth-Moon L1 and L2 libration points could support lunar surface operations and serve as staging areas for future missions to near-Earth asteroids as well as Mars. In fact, an Earth-Moon L2 libration point orbit has been proposed as a potential hub for excursions to Mars as well as activities in support of planetary exploration. Yet, the dynamical environment within the Earth-Moon system is complex and, consequently, trajectory design in the vicinity of Earth-Moon L1 and L2 is nontrivial. Routine transfers between an Earth-Moon L1/L2 facility and Mars also requires design strategies to deliver trajectory arcs that are characterized by a coupling between different multi-body gravitational environments across two-, three- and four body systems. This investigation employs an approach to solve the general problem for transfers from the Earth-Moon libration point orbits to a destination object. Mars, Jupiter, and a near-Earth asteroid (2006RH120) are incorporated as sample destination objects, and general trajectory design procedures for multiple transfer scenarios including manifold and non-manifold options are developed by utilizing simplified models based on the knowledge of the circular restricted three-body problem. Then, the solutions are transitioned to higher-fidelity models; results for multiple departure/arrival scenarios are compared.

Degree Type

Dissertation

Degree Name

Doctor of Philosophy (PhD)

Department

Aeronautics and Astronautics

Date of Award

Spring 2015

First Advisor

Kathleen C. Howell

Committee Member 1

James M. Longuski

Committee Member 2

M. Corless

Committee Member 3

Anil Bajaj

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