Lunar lander propellant production for a multiple site exploration mission
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Earth, Atmospheric, and Planetary Sciences, 2004.
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| Format: | Thesis |
| Language: | en_US |
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Massachusetts Institute of Technology
2005
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| Online Access: | http://hdl.handle.net/1721.1/28613 |
| _version_ | 1826198073283444736 |
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| author | Neubert, Joshua, 1981- |
| author2 | Jeffrey Hoffman. |
| author_facet | Jeffrey Hoffman. Neubert, Joshua, 1981- |
| author_sort | Neubert, Joshua, 1981- |
| collection | MIT |
| description | Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Earth, Atmospheric, and Planetary Sciences, 2004. |
| first_indexed | 2024-09-23T10:58:26Z |
| format | Thesis |
| id | mit-1721.1/28613 |
| institution | Massachusetts Institute of Technology |
| language | en_US |
| last_indexed | 2024-09-23T10:58:26Z |
| publishDate | 2005 |
| publisher | Massachusetts Institute of Technology |
| record_format | dspace |
| spelling | mit-1721.1/286132019-04-12T21:58:31Z Lunar lander propellant production for a multiple site exploration mission Neubert, Joshua, 1981- Jeffrey Hoffman. Massachusetts Institute of Technology. Dept. of Earth, Atmospheric, and Planetary Sciences. Massachusetts Institute of Technology. Dept. of Earth, Atmospheric, and Planetary Sciences. Earth, Atmospheric, and Planetary Sciences. Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Earth, Atmospheric, and Planetary Sciences, 2004. Includes bibliographical references (p. 142-143). A model has been developed to analyze the benefit of utilizing a processing plant architecture so that a lunar oxygen production demonstration mission can also provide a significant exploration and scientific return. This architecture will send one lander to the lunar surface with the capability of producing its own propellant to launch itself to multiple sites of scientific interest. It is compared with two other possible planetary exploration architectures: the multiple mission architecture which sends one mission to each landing site of interest, and the fully fueled architecture which sends one mission with enough propellant to launch itself to all selected landing sites. A value of the total mass savings of the processing plant architecture over these two architectures is used as a means of quantifying the benefit for future lunar exploration. The mass of the power system is found, to be the dominant component of the overall system mass for all cases using a Cassini type : RTG. Results from model runs have shown that at Cassini RTG efficiencies this architecture will not be beneficial in highland regions; however, a significant benefit is shown when using mare and glassy type feedstocks. Further data and analysis is needed to confirm the extent of this benefit. At Cassini RTG efficiencies, a processing plant architecture exhibits significant benefit in mare regions when launching once every [approximately] 2 months or longer. Launching every 2 months creates a benefit for a minimum of 12 launches with a launch range of up to [approximately] 10km. Using pyroclastic glasses as the feedstock produces a benefit when launching once every [approximately] 2 months or longer as well. Launching every 2 months creates a benefit for a minimum of 12 launches (cont.) with a launch range up to [approximately] 13km. Utilizing a longer time between launches significantly increases the launch capabilities. In the near future, RTGs are expected to quadruple in efficiency. With the expected RTG efficiencies the processing plant architecture has an even higher range of benefit for mare and glassy feedstocks. Highland region exploration is only expected to be beneficial with this architecture if further advances in RTG efficiency are made and if system degradation is not severe over a mission timeframe of several years. Advanced RTG technology is identified as the primary technology of need for increasing the benefit of possible processing plant missions. Future versions of this model will be created to better understand and quantify the exact benefit and system dynamics of this architecture. by Joshua Neubert. S.M. 2005-09-27T17:19:14Z 2005-09-27T17:19:14Z 2004 2004 Thesis http://hdl.handle.net/1721.1/28613 57560384 en_US M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission. http://dspace.mit.edu/handle/1721.1/7582 143 p. 9667957 bytes 9686781 bytes application/pdf application/pdf application/pdf Massachusetts Institute of Technology |
| spellingShingle | Earth, Atmospheric, and Planetary Sciences. Neubert, Joshua, 1981- Lunar lander propellant production for a multiple site exploration mission |
| title | Lunar lander propellant production for a multiple site exploration mission |
| title_full | Lunar lander propellant production for a multiple site exploration mission |
| title_fullStr | Lunar lander propellant production for a multiple site exploration mission |
| title_full_unstemmed | Lunar lander propellant production for a multiple site exploration mission |
| title_short | Lunar lander propellant production for a multiple site exploration mission |
| title_sort | lunar lander propellant production for a multiple site exploration mission |
| topic | Earth, Atmospheric, and Planetary Sciences. |
| url | http://hdl.handle.net/1721.1/28613 |
| work_keys_str_mv | AT neubertjoshua1981 lunarlanderpropellantproductionforamultiplesiteexplorationmission |