Lunar CubeSat Impact Trajectory Characteristics as a Function of Its Release Conditions
As a part of early system design activities, trajectory characteristics for a lunar CubeSat impactor mission as a function of its release conditions are analyzed. The goal of this mission is to take measurements of surface magnetic fields to study lunar magnetic anomalies. To deploy the CubeSat impa...
Gespeichert in:
| Veröffentlicht in: | Mathematical problems in engineering 2015-01, Vol.2015 (2015), p.1-16 |
|---|---|
| Hauptverfasser: | , , |
| Format: | Artikel |
| Sprache: | eng |
| Schlagworte: | |
| Online-Zugang: | Volltext |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | 16 |
|---|---|
| container_issue | 2015 |
| container_start_page | 1 |
| container_title | Mathematical problems in engineering |
| container_volume | 2015 |
| creator | Song, Young-Joo Garick-Bethell, Ian Jin, Ho |
| description | As a part of early system design activities, trajectory characteristics for a lunar CubeSat impactor mission as a function of its release conditions are analyzed. The goal of this mission is to take measurements of surface magnetic fields to study lunar magnetic anomalies. To deploy the CubeSat impactor, a mother-ship is assumed to have a circular polar orbit with inclination of 90 degrees at a 100 km altitude at the Moon. Both the in- and out-of-plane direction deploy angles as well as delta-V magnitudes are considered for the CubeSat release conditions. All necessary parameters required at the early design phase are analyzed, including CubeSat flight time to reach the lunar surface, impact velocity, cross ranges distance, and associated impact angles, which are all directly affected by the CubeSat release conditions. Also, relative motions between these two satellites are analyzed for communication and navigation purposes. Although the current analysis is only focused on a lunar impactor mission, the methods described in this work can easily be modified and applied to any future planetary impactor missions with CubeSat-based payloads. |
| doi_str_mv | 10.1155/2015/681901 |
| format | Article |
| fullrecord | <record><control><sourceid>proquest_cross</sourceid><recordid>TN_cdi_proquest_miscellaneous_1685787075</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>3666094521</sourcerecordid><originalsourceid>FETCH-LOGICAL-c389t-fc36e5e6b6914f9f035996f816d6b9e0e3b65aa00a4b6a8289e6f3d1c7126b933</originalsourceid><addsrcrecordid>eNqF0FFLwzAQB_AiCs7pk-8S8EWUulzTpOmjFKeDgaATfStpesGOrp1Jiuzbm1EfxBfh4I7kx3H8o-gc6C0A57OEAp8JCTmFg2gCXLCYQ5odhpkmaQwJez-OTpxbU5oABzmJ3pZDpywphgpflCeLzVZpT1ZWrVH73u5I8aFseELbON9oR1QoMh867Zu-I70hC-_IM7aoHJKi7-pm_-FOoyOjWodnP30avc7vV8VjvHx6WBR3y1gzmfvYaCaQo6hEDqnJDWU8z4WRIGpR5UiRVYIrRalKK6FkInMUhtWgM0gCYGwaXY17t7b_HND5ctM4jW2rOuwHV4KQPJMZzXigl3_ouh9sF64LKuNhOadJUDej0rZ3zqIpt7bZKLsrgZb7kMt9yOUYctDXo_5oulp9Nf_gixFjIGjUL5ylKU_YNxPehCc</addsrcrecordid><sourcetype>Aggregation Database</sourcetype><iscdi>true</iscdi><recordtype>article</recordtype><pqid>1675828502</pqid></control><display><type>article</type><title>Lunar CubeSat Impact Trajectory Characteristics as a Function of Its Release Conditions</title><source>Wiley Online Library Open Access</source><source>EZB-FREE-00999 freely available EZB journals</source><source>Alma/SFX Local Collection</source><creator>Song, Young-Joo ; Garick-Bethell, Ian ; Jin, Ho</creator><contributor>Xie, Gongnan</contributor><creatorcontrib>Song, Young-Joo ; Garick-Bethell, Ian ; Jin, Ho ; Xie, Gongnan</creatorcontrib><description>As a part of early system design activities, trajectory characteristics for a lunar CubeSat impactor mission as a function of its release conditions are analyzed. The goal of this mission is to take measurements of surface magnetic fields to study lunar magnetic anomalies. To deploy the CubeSat impactor, a mother-ship is assumed to have a circular polar orbit with inclination of 90 degrees at a 100 km altitude at the Moon. Both the in- and out-of-plane direction deploy angles as well as delta-V magnitudes are considered for the CubeSat release conditions. All necessary parameters required at the early design phase are analyzed, including CubeSat flight time to reach the lunar surface, impact velocity, cross ranges distance, and associated impact angles, which are all directly affected by the CubeSat release conditions. Also, relative motions between these two satellites are analyzed for communication and navigation purposes. Although the current analysis is only focused on a lunar impactor mission, the methods described in this work can easily be modified and applied to any future planetary impactor missions with CubeSat-based payloads.</description><identifier>ISSN: 1024-123X</identifier><identifier>EISSN: 1563-5147</identifier><identifier>DOI: 10.1155/2015/681901</identifier><language>eng</language><publisher>Cairo, Egypt: Hindawi Publishing Corporation</publisher><subject>Aeronautics ; Communication satellites ; Cubesat ; Design analysis ; Design parameters ; Flight time ; Functions (mathematics) ; Impact analysis ; Impact velocity ; Impactors ; Lunar surface ; Magnetic anomalies ; Magnetic fields ; Mathematical analysis ; Mathematical problems ; Missions ; Moon ; Observatories ; Parameter modification ; Payloads ; Polar orbits ; Radiation ; Science ; Solar system ; Space exploration ; Space missions ; Systems design ; Trajectories ; Trajectory analysis ; Trajectory measurement</subject><ispartof>Mathematical problems in engineering, 2015-01, Vol.2015 (2015), p.1-16</ispartof><rights>Copyright © 2015 Young-Joo Song et al.</rights><rights>Copyright © 2015 Young-Joo Song et al. Young-Joo Song et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.</rights><lds50>peer_reviewed</lds50><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c389t-fc36e5e6b6914f9f035996f816d6b9e0e3b65aa00a4b6a8289e6f3d1c7126b933</citedby><cites>FETCH-LOGICAL-c389t-fc36e5e6b6914f9f035996f816d6b9e0e3b65aa00a4b6a8289e6f3d1c7126b933</cites><orcidid>0000-0002-1773-8234</orcidid></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,776,780,27903,27904</link.rule.ids></links><search><contributor>Xie, Gongnan</contributor><creatorcontrib>Song, Young-Joo</creatorcontrib><creatorcontrib>Garick-Bethell, Ian</creatorcontrib><creatorcontrib>Jin, Ho</creatorcontrib><title>Lunar CubeSat Impact Trajectory Characteristics as a Function of Its Release Conditions</title><title>Mathematical problems in engineering</title><description>As a part of early system design activities, trajectory characteristics for a lunar CubeSat impactor mission as a function of its release conditions are analyzed. The goal of this mission is to take measurements of surface magnetic fields to study lunar magnetic anomalies. To deploy the CubeSat impactor, a mother-ship is assumed to have a circular polar orbit with inclination of 90 degrees at a 100 km altitude at the Moon. Both the in- and out-of-plane direction deploy angles as well as delta-V magnitudes are considered for the CubeSat release conditions. All necessary parameters required at the early design phase are analyzed, including CubeSat flight time to reach the lunar surface, impact velocity, cross ranges distance, and associated impact angles, which are all directly affected by the CubeSat release conditions. Also, relative motions between these two satellites are analyzed for communication and navigation purposes. Although the current analysis is only focused on a lunar impactor mission, the methods described in this work can easily be modified and applied to any future planetary impactor missions with CubeSat-based payloads.</description><subject>Aeronautics</subject><subject>Communication satellites</subject><subject>Cubesat</subject><subject>Design analysis</subject><subject>Design parameters</subject><subject>Flight time</subject><subject>Functions (mathematics)</subject><subject>Impact analysis</subject><subject>Impact velocity</subject><subject>Impactors</subject><subject>Lunar surface</subject><subject>Magnetic anomalies</subject><subject>Magnetic fields</subject><subject>Mathematical analysis</subject><subject>Mathematical problems</subject><subject>Missions</subject><subject>Moon</subject><subject>Observatories</subject><subject>Parameter modification</subject><subject>Payloads</subject><subject>Polar orbits</subject><subject>Radiation</subject><subject>Science</subject><subject>Solar system</subject><subject>Space exploration</subject><subject>Space missions</subject><subject>Systems design</subject><subject>Trajectories</subject><subject>Trajectory analysis</subject><subject>Trajectory measurement</subject><issn>1024-123X</issn><issn>1563-5147</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2015</creationdate><recordtype>article</recordtype><sourceid>RHX</sourceid><sourceid>ABUWG</sourceid><sourceid>AFKRA</sourceid><sourceid>AZQEC</sourceid><sourceid>BENPR</sourceid><sourceid>CCPQU</sourceid><sourceid>DWQXO</sourceid><sourceid>GNUQQ</sourceid><recordid>eNqF0FFLwzAQB_AiCs7pk-8S8EWUulzTpOmjFKeDgaATfStpesGOrp1Jiuzbm1EfxBfh4I7kx3H8o-gc6C0A57OEAp8JCTmFg2gCXLCYQ5odhpkmaQwJez-OTpxbU5oABzmJ3pZDpywphgpflCeLzVZpT1ZWrVH73u5I8aFseELbON9oR1QoMh867Zu-I70hC-_IM7aoHJKi7-pm_-FOoyOjWodnP30avc7vV8VjvHx6WBR3y1gzmfvYaCaQo6hEDqnJDWU8z4WRIGpR5UiRVYIrRalKK6FkInMUhtWgM0gCYGwaXY17t7b_HND5ctM4jW2rOuwHV4KQPJMZzXigl3_ouh9sF64LKuNhOadJUDej0rZ3zqIpt7bZKLsrgZb7kMt9yOUYctDXo_5oulp9Nf_gixFjIGjUL5ylKU_YNxPehCc</recordid><startdate>20150101</startdate><enddate>20150101</enddate><creator>Song, Young-Joo</creator><creator>Garick-Bethell, Ian</creator><creator>Jin, Ho</creator><general>Hindawi Publishing Corporation</general><general>Hindawi Limited</general><scope>ADJCN</scope><scope>AHFXO</scope><scope>RHU</scope><scope>RHW</scope><scope>RHX</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>8FE</scope><scope>8FG</scope><scope>ABJCF</scope><scope>ABUWG</scope><scope>AFKRA</scope><scope>ARAPS</scope><scope>AZQEC</scope><scope>BENPR</scope><scope>BGLVJ</scope><scope>CCPQU</scope><scope>CWDGH</scope><scope>DWQXO</scope><scope>FR3</scope><scope>GNUQQ</scope><scope>HCIFZ</scope><scope>JQ2</scope><scope>K7-</scope><scope>KR7</scope><scope>L6V</scope><scope>M7S</scope><scope>P5Z</scope><scope>P62</scope><scope>PIMPY</scope><scope>PQEST</scope><scope>PQQKQ</scope><scope>PQUKI</scope><scope>PRINS</scope><scope>PTHSS</scope><scope>H8D</scope><scope>L7M</scope><orcidid>https://orcid.org/0000-0002-1773-8234</orcidid></search><sort><creationdate>20150101</creationdate><title>Lunar CubeSat Impact Trajectory Characteristics as a Function of Its Release Conditions</title><author>Song, Young-Joo ; Garick-Bethell, Ian ; Jin, Ho</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c389t-fc36e5e6b6914f9f035996f816d6b9e0e3b65aa00a4b6a8289e6f3d1c7126b933</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2015</creationdate><topic>Aeronautics</topic><topic>Communication satellites</topic><topic>Cubesat</topic><topic>Design analysis</topic><topic>Design parameters</topic><topic>Flight time</topic><topic>Functions (mathematics)</topic><topic>Impact analysis</topic><topic>Impact velocity</topic><topic>Impactors</topic><topic>Lunar surface</topic><topic>Magnetic anomalies</topic><topic>Magnetic fields</topic><topic>Mathematical analysis</topic><topic>Mathematical problems</topic><topic>Missions</topic><topic>Moon</topic><topic>Observatories</topic><topic>Parameter modification</topic><topic>Payloads</topic><topic>Polar orbits</topic><topic>Radiation</topic><topic>Science</topic><topic>Solar system</topic><topic>Space exploration</topic><topic>Space missions</topic><topic>Systems design</topic><topic>Trajectories</topic><topic>Trajectory analysis</topic><topic>Trajectory measurement</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Song, Young-Joo</creatorcontrib><creatorcontrib>Garick-Bethell, Ian</creatorcontrib><creatorcontrib>Jin, Ho</creatorcontrib><collection>الدوريات العلمية والإحصائية - e-Marefa Academic and Statistical Periodicals</collection><collection>معرفة - المحتوى العربي الأكاديمي المتكامل - e-Marefa Academic Complete</collection><collection>Hindawi Publishing Complete</collection><collection>Hindawi Publishing Subscription Journals</collection><collection>Hindawi Publishing Open Access</collection><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>ProQuest SciTech Collection</collection><collection>ProQuest Technology Collection</collection><collection>Materials Science & Engineering Collection</collection><collection>ProQuest Central (Alumni Edition)</collection><collection>ProQuest Central UK/Ireland</collection><collection>Advanced Technologies & Aerospace Collection</collection><collection>ProQuest Central Essentials</collection><collection>ProQuest Central</collection><collection>Technology Collection</collection><collection>ProQuest One Community College</collection><collection>Middle East & Africa Database</collection><collection>ProQuest Central Korea</collection><collection>Engineering Research Database</collection><collection>ProQuest Central Student</collection><collection>SciTech Premium Collection</collection><collection>ProQuest Computer Science Collection</collection><collection>Computer Science Database</collection><collection>Civil Engineering Abstracts</collection><collection>ProQuest Engineering Collection</collection><collection>Engineering Database</collection><collection>Advanced Technologies & Aerospace Database</collection><collection>ProQuest Advanced Technologies & Aerospace Collection</collection><collection>Publicly Available Content Database</collection><collection>ProQuest One Academic Eastern Edition (DO NOT USE)</collection><collection>ProQuest One Academic</collection><collection>ProQuest One Academic UKI Edition</collection><collection>ProQuest Central China</collection><collection>Engineering Collection</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Mathematical problems in engineering</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Song, Young-Joo</au><au>Garick-Bethell, Ian</au><au>Jin, Ho</au><au>Xie, Gongnan</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Lunar CubeSat Impact Trajectory Characteristics as a Function of Its Release Conditions</atitle><jtitle>Mathematical problems in engineering</jtitle><date>2015-01-01</date><risdate>2015</risdate><volume>2015</volume><issue>2015</issue><spage>1</spage><epage>16</epage><pages>1-16</pages><issn>1024-123X</issn><eissn>1563-5147</eissn><abstract>As a part of early system design activities, trajectory characteristics for a lunar CubeSat impactor mission as a function of its release conditions are analyzed. The goal of this mission is to take measurements of surface magnetic fields to study lunar magnetic anomalies. To deploy the CubeSat impactor, a mother-ship is assumed to have a circular polar orbit with inclination of 90 degrees at a 100 km altitude at the Moon. Both the in- and out-of-plane direction deploy angles as well as delta-V magnitudes are considered for the CubeSat release conditions. All necessary parameters required at the early design phase are analyzed, including CubeSat flight time to reach the lunar surface, impact velocity, cross ranges distance, and associated impact angles, which are all directly affected by the CubeSat release conditions. Also, relative motions between these two satellites are analyzed for communication and navigation purposes. Although the current analysis is only focused on a lunar impactor mission, the methods described in this work can easily be modified and applied to any future planetary impactor missions with CubeSat-based payloads.</abstract><cop>Cairo, Egypt</cop><pub>Hindawi Publishing Corporation</pub><doi>10.1155/2015/681901</doi><tpages>16</tpages><orcidid>https://orcid.org/0000-0002-1773-8234</orcidid><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext |
| identifier | ISSN: 1024-123X |
| ispartof | Mathematical problems in engineering, 2015-01, Vol.2015 (2015), p.1-16 |
| issn | 1024-123X 1563-5147 |
| language | eng |
| recordid | cdi_proquest_miscellaneous_1685787075 |
| source | Wiley Online Library Open Access; EZB-FREE-00999 freely available EZB journals; Alma/SFX Local Collection |
| subjects | Aeronautics Communication satellites Cubesat Design analysis Design parameters Flight time Functions (mathematics) Impact analysis Impact velocity Impactors Lunar surface Magnetic anomalies Magnetic fields Mathematical analysis Mathematical problems Missions Moon Observatories Parameter modification Payloads Polar orbits Radiation Science Solar system Space exploration Space missions Systems design Trajectories Trajectory analysis Trajectory measurement |
| title | Lunar CubeSat Impact Trajectory Characteristics as a Function of Its Release Conditions |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-24T01%3A01%3A52IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-proquest_cross&rft_val_fmt=info:ofi/fmt:kev:mtx:journal&rft.genre=article&rft.atitle=Lunar%20CubeSat%20Impact%20Trajectory%20Characteristics%20as%20a%20Function%20of%20Its%20Release%20Conditions&rft.jtitle=Mathematical%20problems%20in%20engineering&rft.au=Song,%20Young-Joo&rft.date=2015-01-01&rft.volume=2015&rft.issue=2015&rft.spage=1&rft.epage=16&rft.pages=1-16&rft.issn=1024-123X&rft.eissn=1563-5147&rft_id=info:doi/10.1155/2015/681901&rft_dat=%3Cproquest_cross%3E3666094521%3C/proquest_cross%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_pqid=1675828502&rft_id=info:pmid/&rfr_iscdi=true |