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Fuel optimal low thrust trajectories for an asteroid sample return mission

This thesis explores how an Asteroid Sample Return Mission might make use of solar electric propulsion to send a spacecraft on a journey to the asteroid 1989ML and back. It examines different trajectories that can be used to get an asteroid sample return or similar spacecraft to an interplanetary destination and back in the most fuel-efficient manner. While current plans call for keeping such a spacecraft on the asteroid performing science experiments for approximately 90 days, it is prudent to inquire how lengthening or shortening this time period may affect mission fuel requirements. Using optimal control methods, various mission scenarios have been modeled and simulated. The results suggest that the amount of time that the spacecraft may spend on the asteroid surface can be approximated as a linear function of the available fuel mass. Furthermore, It can be shown that as maximum available thrust is decreased, the radial component of the optimal thrust vector becomes more pronounced.

Identiferoai:union.ndltd.org:nps.edu/oai:calhoun.nps.edu:10945/2242
Date03 1900
CreatorsRust, Jack W.
ContributorsRoss, I. Michael, Weinstein, Stacy, Naval Postgraduate School (U.S.)., Department of Mechanical and Astronautical Engineering
PublisherMonterey, California. Naval Postgraduate School
Source SetsNaval Postgraduate School
Detected LanguageEnglish
TypeThesis
Formatxiv, 59 p. : ill. (some col.) ;, application/pdf
RightsApproved for public release, distribution unlimited

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