Masters Theses

Keywords and Phrases

CR3BP; CubeSat; DV; GMAT; Propulsion; SLS

Abstract

"The CubeSat/small satellite field is one of the fastest growing means of space exploration, with applications continuing to expand for component development, communication, and scientific research. This thesis study focuses on establishing suitable small satellite Earth-to-Moon direct-transfer trajectories, providing a baseline understanding of their propulsive demands, determining currently available off-the-shelf propulsive technology capable of meeting these demands, as well as demonstrating the effectiveness of the Circular Restricted Three Body Problem (CR3BP) for preliminary mission design. Using the CR3BP and derived requirements from NASA's Cube Quest Challenge, five different trajectory scenarios were analyzed for their propulsive requirements. Results indicate that the CR3BP is an effective means for preliminary mission design; however, limitations were noted in its ability to account for the lunar orbit eccentricity with respect to the Earth. Additionally, two available options of off-the-shelf propulsion systems are identified that can achieve the ΔV necessary for lunar capture, but have not yet been demonstrated in-flight"--Abstract, page iii.

Advisor(s)

Pernicka, Henry J.

Committee Member(s)

Riggins, David W.
Hosder, Serhat

Department(s)

Mechanical and Aerospace Engineering

Degree Name

M.S. in Aerospace Engineering

Publisher

Missouri University of Science and Technology

Publication Date

Fall 2019

Pagination

xi, 91 pages

Note about bibliography

Includes bibliographical references (pages 81-90)

Rights

© 2019 Garrett Levi McMillan, All rights reserved.

Document Type

Thesis - Open Access

File Type

text

Language

English

Thesis Number

T 11641

Electronic OCLC #

1139525649

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