Use of Mini-Mag Orion and superconducting coils for near-term interstellar transportation
Interstellar transportation to nearby star systems over periods shorter than the human lifetime requires speeds in the range of 0.1–0.15 c and relatively high accelerations. These speeds are not attainable using rockets, even with advanced fusion engines because at these velocities, the energy densi...
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description | Interstellar transportation to nearby star systems over periods shorter than the human lifetime requires speeds in the range of 0.1–0.15
c and relatively high accelerations. These speeds are not attainable using rockets, even with advanced fusion engines because at these velocities, the energy density of the spacecraft approaches the energy density of the fuel. Anti-matter engines are theoretically possible but current physical limitations would have to be suspended to get the mass densities required. Interstellar ramjets have not proven practicable, so this leaves beamed momentum propulsion or a continuously fueled Mag-Orion system as the remaining candidates. However, deceleration is also a major issue, but part of the Mini-Mag Orion approach assists in solving this problem. This paper reviews the state of the art from a Phases I and II SBIT between Sandia National Laboratories and Andrews Space, applying our results to near-term interstellar travel.
A 1000
T crewed spacecraft and propulsion system dry mass at
.1
c
contains
∼
9
×
10
21
J
. The author has generated technology requirements elsewhere for use of fission power reactors and conventional Brayton cycle machinery to propel a spacecraft using electric propulsion. Here we replace the electric power conversion, radiators, power generators and electric thrusters with a Mini-Mag Orion fission–fusion hybrid. Only a small fraction of fission fuel is actually carried with the spacecraft, the remainder of the propellant (macro-particles of fissionable material with a D-T core) is beamed to the spacecraft, and the total beam energy requirement for an interstellar probe mission is roughly
10
20
J
, which would require the complete fissioning of 1000
ton of Uranium assuming 35% power plant efficiency. This is roughly equivalent to a recurring cost per flight of 3.0 billion dollars in reactor grade enriched uranium using today's prices. Therefore, interstellar flight is an expensive proposition, but not unaffordable, if the nonrecurring costs of building the power plant can be minimized. |
doi_str_mv | 10.1016/j.actaastro.2007.01.052 |
format | Article |
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c and relatively high accelerations. These speeds are not attainable using rockets, even with advanced fusion engines because at these velocities, the energy density of the spacecraft approaches the energy density of the fuel. Anti-matter engines are theoretically possible but current physical limitations would have to be suspended to get the mass densities required. Interstellar ramjets have not proven practicable, so this leaves beamed momentum propulsion or a continuously fueled Mag-Orion system as the remaining candidates. However, deceleration is also a major issue, but part of the Mini-Mag Orion approach assists in solving this problem. This paper reviews the state of the art from a Phases I and II SBIT between Sandia National Laboratories and Andrews Space, applying our results to near-term interstellar travel.
A 1000
T crewed spacecraft and propulsion system dry mass at
.1
c
contains
∼
9
×
10
21
J
. The author has generated technology requirements elsewhere for use of fission power reactors and conventional Brayton cycle machinery to propel a spacecraft using electric propulsion. Here we replace the electric power conversion, radiators, power generators and electric thrusters with a Mini-Mag Orion fission–fusion hybrid. Only a small fraction of fission fuel is actually carried with the spacecraft, the remainder of the propellant (macro-particles of fissionable material with a D-T core) is beamed to the spacecraft, and the total beam energy requirement for an interstellar probe mission is roughly
10
20
J
, which would require the complete fissioning of 1000
ton of Uranium assuming 35% power plant efficiency. This is roughly equivalent to a recurring cost per flight of 3.0 billion dollars in reactor grade enriched uranium using today's prices. Therefore, interstellar flight is an expensive proposition, but not unaffordable, if the nonrecurring costs of building the power plant can be minimized.</description><identifier>ISSN: 0094-5765</identifier><identifier>EISSN: 1879-2030</identifier><identifier>DOI: 10.1016/j.actaastro.2007.01.052</identifier><language>eng</language><publisher>Elsevier Ltd</publisher><subject>Density ; Electric power generation ; Electric power plants ; Energy density ; Interstellar Probe Mission (NASA) ; Interstellar travel ; Spacecraft ; Uranium</subject><ispartof>Acta astronautica, 2007-06, Vol.61 (1), p.450-458</ispartof><rights>2007</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c408t-fb9bdff47f9c42a378a32fedc120c4757963f76efb8ab8087e0922df6a4d43a73</citedby><cites>FETCH-LOGICAL-c408t-fb9bdff47f9c42a378a32fedc120c4757963f76efb8ab8087e0922df6a4d43a73</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://dx.doi.org/10.1016/j.actaastro.2007.01.052$$EHTML$$P50$$Gelsevier$$H</linktohtml><link.rule.ids>314,780,784,3548,27923,27924,45994</link.rule.ids></links><search><creatorcontrib>Lenard, Roger X.</creatorcontrib><creatorcontrib>Andrews, Dana G.</creatorcontrib><title>Use of Mini-Mag Orion and superconducting coils for near-term interstellar transportation</title><title>Acta astronautica</title><description>Interstellar transportation to nearby star systems over periods shorter than the human lifetime requires speeds in the range of 0.1–0.15
c and relatively high accelerations. These speeds are not attainable using rockets, even with advanced fusion engines because at these velocities, the energy density of the spacecraft approaches the energy density of the fuel. Anti-matter engines are theoretically possible but current physical limitations would have to be suspended to get the mass densities required. Interstellar ramjets have not proven practicable, so this leaves beamed momentum propulsion or a continuously fueled Mag-Orion system as the remaining candidates. However, deceleration is also a major issue, but part of the Mini-Mag Orion approach assists in solving this problem. This paper reviews the state of the art from a Phases I and II SBIT between Sandia National Laboratories and Andrews Space, applying our results to near-term interstellar travel.
A 1000
T crewed spacecraft and propulsion system dry mass at
.1
c
contains
∼
9
×
10
21
J
. The author has generated technology requirements elsewhere for use of fission power reactors and conventional Brayton cycle machinery to propel a spacecraft using electric propulsion. Here we replace the electric power conversion, radiators, power generators and electric thrusters with a Mini-Mag Orion fission–fusion hybrid. Only a small fraction of fission fuel is actually carried with the spacecraft, the remainder of the propellant (macro-particles of fissionable material with a D-T core) is beamed to the spacecraft, and the total beam energy requirement for an interstellar probe mission is roughly
10
20
J
, which would require the complete fissioning of 1000
ton of Uranium assuming 35% power plant efficiency. This is roughly equivalent to a recurring cost per flight of 3.0 billion dollars in reactor grade enriched uranium using today's prices. Therefore, interstellar flight is an expensive proposition, but not unaffordable, if the nonrecurring costs of building the power plant can be minimized.</description><subject>Density</subject><subject>Electric power generation</subject><subject>Electric power plants</subject><subject>Energy density</subject><subject>Interstellar Probe Mission (NASA)</subject><subject>Interstellar travel</subject><subject>Spacecraft</subject><subject>Uranium</subject><issn>0094-5765</issn><issn>1879-2030</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2007</creationdate><recordtype>article</recordtype><recordid>eNqNkUtrGzEUhUVIIY6b3xCtspvJ1WNG0jKYviAmm2bRlZA1V0HGlhxJLvTfd4xLt87qbL5zuNyPkHsGPQM2Pm5755tztZXccwDVA-th4FdkwbQyHQcB12QBYGQ3qHG4Ibe1bmEGuTYL8uu1Is2BrmOK3dq90ZcSc6IuTbQeD1h8TtPRt5jeqM9xV2nIhSZ0pWtY9jSmOWrD3c4V2opL9ZBLc23e-Ew-BberePcvl-T165efq-_d88u3H6un585L0K0LG7OZQpAqGC-5E0o7wQNOnnHwUg3KjCKoEcNGu40GrRAM51MYnZykcEosycN591Dy-xFrs_tY_emihPlYLTdGaMHEZRA0l8MgPwDyUYEYZ1CdQV9yrQWDPZS4d-WPZWBPcuzW_pdjT3IsMDvLmZtP5ybOn_kdsdjqIyaPUyzom51yvLjxF4aBnh8</recordid><startdate>20070601</startdate><enddate>20070601</enddate><creator>Lenard, Roger X.</creator><creator>Andrews, Dana G.</creator><general>Elsevier Ltd</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7TG</scope><scope>KL.</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope></search><sort><creationdate>20070601</creationdate><title>Use of Mini-Mag Orion and superconducting coils for near-term interstellar transportation</title><author>Lenard, Roger X. ; Andrews, Dana G.</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c408t-fb9bdff47f9c42a378a32fedc120c4757963f76efb8ab8087e0922df6a4d43a73</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2007</creationdate><topic>Density</topic><topic>Electric power generation</topic><topic>Electric power plants</topic><topic>Energy density</topic><topic>Interstellar Probe Mission (NASA)</topic><topic>Interstellar travel</topic><topic>Spacecraft</topic><topic>Uranium</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Lenard, Roger X.</creatorcontrib><creatorcontrib>Andrews, Dana G.</creatorcontrib><collection>CrossRef</collection><collection>Meteorological & Geoastrophysical Abstracts</collection><collection>Meteorological & Geoastrophysical Abstracts - Academic</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Acta astronautica</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Lenard, Roger X.</au><au>Andrews, Dana G.</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Use of Mini-Mag Orion and superconducting coils for near-term interstellar transportation</atitle><jtitle>Acta astronautica</jtitle><date>2007-06-01</date><risdate>2007</risdate><volume>61</volume><issue>1</issue><spage>450</spage><epage>458</epage><pages>450-458</pages><issn>0094-5765</issn><eissn>1879-2030</eissn><abstract>Interstellar transportation to nearby star systems over periods shorter than the human lifetime requires speeds in the range of 0.1–0.15
c and relatively high accelerations. These speeds are not attainable using rockets, even with advanced fusion engines because at these velocities, the energy density of the spacecraft approaches the energy density of the fuel. Anti-matter engines are theoretically possible but current physical limitations would have to be suspended to get the mass densities required. Interstellar ramjets have not proven practicable, so this leaves beamed momentum propulsion or a continuously fueled Mag-Orion system as the remaining candidates. However, deceleration is also a major issue, but part of the Mini-Mag Orion approach assists in solving this problem. This paper reviews the state of the art from a Phases I and II SBIT between Sandia National Laboratories and Andrews Space, applying our results to near-term interstellar travel.
A 1000
T crewed spacecraft and propulsion system dry mass at
.1
c
contains
∼
9
×
10
21
J
. The author has generated technology requirements elsewhere for use of fission power reactors and conventional Brayton cycle machinery to propel a spacecraft using electric propulsion. Here we replace the electric power conversion, radiators, power generators and electric thrusters with a Mini-Mag Orion fission–fusion hybrid. Only a small fraction of fission fuel is actually carried with the spacecraft, the remainder of the propellant (macro-particles of fissionable material with a D-T core) is beamed to the spacecraft, and the total beam energy requirement for an interstellar probe mission is roughly
10
20
J
, which would require the complete fissioning of 1000
ton of Uranium assuming 35% power plant efficiency. This is roughly equivalent to a recurring cost per flight of 3.0 billion dollars in reactor grade enriched uranium using today's prices. Therefore, interstellar flight is an expensive proposition, but not unaffordable, if the nonrecurring costs of building the power plant can be minimized.</abstract><pub>Elsevier Ltd</pub><doi>10.1016/j.actaastro.2007.01.052</doi><tpages>9</tpages></addata></record> |
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source | ScienceDirect Journals (5 years ago - present) |
subjects | Density Electric power generation Electric power plants Energy density Interstellar Probe Mission (NASA) Interstellar travel Spacecraft Uranium |
title | Use of Mini-Mag Orion and superconducting coils for near-term interstellar transportation |
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