Techn. Univ., Diss.--Braunschweig, 2003.

Thesis (M.S.)--University of Missouri-Columbia, 2004. / Typescript. Includes bibliographical references (leaves 59-61). Also available on the Internet.

Thesis (M.S.)--University of Michigan, 1979.

Thesis (Ph. D.)--University of Texas at Austin, 1998. / Vita. Includes bibliographical references (leaves 214-224). Available also in a digital version from Dissertation Abstracts.

Thesis (M.S.)--California Polytechnic State University, 2009. / Title from PDF title page; viewed on Sept. 16, 2009. "August 2009." "In partial fulfillment of the requirements for the degree [of] Master of Science in Mechanical Engineering." "Presented to the faculty of California Polytechnic State University, San Luis Obispo." Major professor: Andrew Kean, Ph.D. Includes bibliographical references (p. 71-72).

Thesis (M.S. in Systems Engineering)--Naval Postgraduate School, June 2005. / Thesis Advisor(s): Roberto Cristi. Includes bibliographical references (p. 71-72). Also available online.

Thesis (M.S.)--University of Missouri-Columbia, 2004. / Typescript. Includes bibliographical references (leaves 59-61). Also available on the Internet.

Thesis (M.S.)--University of Missouri--Rolla, 2007. / Vita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed May 11, 2007) Includes bibliographical references (p. 115-119).

M.Ing. (Mechanical Engineering) / Please refer to full text to view abstract

The experiences of the Apollo lunar landings revealed the danger lunar dust can pose to surrounding hardware, outposts, and orbiting spacecraft. Future lunar missions such as the Artemis program will require more information about the trajectories of ejecta blown by landers to protect orbiting spacecraft such as the Lunar Gateway. In this paper, we simulate lunar lander ejecta trajectories using the Mercury N-body integrator. We placed cones of test particles on the Moon at the North Pole, South Pole, and Equator with various ejection speeds and angles. The results show that particles ejected at speeds near the Moon's escape velocity can take from several days to weeks to re-impact the lunar surface. The time particles spend in the vicinity of the Moon varies mostly by location. Particles stay aloft after 30 days at launch speeds as low as 2.142 km/s when launched from the Equator. Number density maps and flux density maps of the particle trajectories reveal that particles launched from the South Pole are likely to impact the Lunar Gateway at its orbit near periselene at ejection speeds as low as 2.142 km/s. Particles launched from the Equator also reach the altitude of the Gateway orbit. Particles ejected from the North Pole can impact the Gateway along its orbit at ejections speeds somewhere between 2.3324 and 2.3562 km/s.