One-rocket multi-satellite layout method and system based on separation safety design
The invention relates to a one-rocket multi-satellite layout method and system based on separation safety design, and the method comprises the steps: obtaining the orbit injection attitude deviation at a satellite-rocket separation moment, and setting an initial separation state; setting mass center...
Gespeichert in:
| Hauptverfasser: | , , , , , , , , , , |
|---|---|
| Format: | Patent |
| Sprache: | chi ; eng |
| Schlagworte: | |
| Online-Zugang: | Volltext bestellen |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | |
|---|---|
| container_issue | |
| container_start_page | |
| container_title | |
| container_volume | |
| creator | ZHAO WEN CHEN SHIQIANG ZHANG RAN XU SHANSHU LI JINGLIN LI JUN GU MINGKUN LIU YIN LYU PENGWEI SHI YAOXIN WU HANXIAO |
| description | The invention relates to a one-rocket multi-satellite layout method and system based on separation safety design, and the method comprises the steps: obtaining the orbit injection attitude deviation at a satellite-rocket separation moment, and setting an initial separation state; setting mass center coordinates of M groups of satellites relative to a rocket body and separation energy of the satellites in an initial separation state, and completing population initialization; establishing a fitness function by taking the minimum far-field distance of the two satellites from the half period to the five periods after separation and the sum of the attitude angular velocities of the satellites after separation as optimization indexes; calculating a fitness function value of each particle; updating an individual extreme value and a global extreme value; updating the particle speed and the particle position; and when a preset ending condition is met, outputting a one-rocket multi-satellite layout optimization result. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_CN117634024A</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>CN117634024A</sourcerecordid><originalsourceid>FETCH-epo_espacenet_CN117634024A3</originalsourceid><addsrcrecordid>eNqNirEKwkAQBa-xEPUf1g84MCZoLUGx0kbrsOZe4uHlLmQ3Rf5eBT_AaoZh5uZ-jbBDql9Q6sag3gorQvAKCjyl8ZOhz-SIoyOZRNHRgwWOUiRBzwOr_yo30IkcxLdxaWYNB8Hqx4VZn4638mzRpwrSc40IrcpLlu13ebHZFof8n-cNBPY5eQ</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>One-rocket multi-satellite layout method and system based on separation safety design</title><source>esp@cenet</source><creator>ZHAO WEN ; CHEN SHIQIANG ; ZHANG RAN ; XU SHANSHU ; LI JINGLIN ; LI JUN ; GU MINGKUN ; LIU YIN ; LYU PENGWEI ; SHI YAOXIN ; WU HANXIAO</creator><creatorcontrib>ZHAO WEN ; CHEN SHIQIANG ; ZHANG RAN ; XU SHANSHU ; LI JINGLIN ; LI JUN ; GU MINGKUN ; LIU YIN ; LYU PENGWEI ; SHI YAOXIN ; WU HANXIAO</creatorcontrib><description>The invention relates to a one-rocket multi-satellite layout method and system based on separation safety design, and the method comprises the steps: obtaining the orbit injection attitude deviation at a satellite-rocket separation moment, and setting an initial separation state; setting mass center coordinates of M groups of satellites relative to a rocket body and separation energy of the satellites in an initial separation state, and completing population initialization; establishing a fitness function by taking the minimum far-field distance of the two satellites from the half period to the five periods after separation and the sum of the attitude angular velocities of the satellites after separation as optimization indexes; calculating a fitness function value of each particle; updating an individual extreme value and a global extreme value; updating the particle speed and the particle position; and when a preset ending condition is met, outputting a one-rocket multi-satellite layout optimization result.</description><language>chi ; eng</language><subject>CALCULATING ; COMPUTING ; COUNTING ; ELECTRIC DIGITAL DATA PROCESSING ; PHYSICS</subject><creationdate>2024</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20240301&DB=EPODOC&CC=CN&NR=117634024A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20240301&DB=EPODOC&CC=CN&NR=117634024A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>ZHAO WEN</creatorcontrib><creatorcontrib>CHEN SHIQIANG</creatorcontrib><creatorcontrib>ZHANG RAN</creatorcontrib><creatorcontrib>XU SHANSHU</creatorcontrib><creatorcontrib>LI JINGLIN</creatorcontrib><creatorcontrib>LI JUN</creatorcontrib><creatorcontrib>GU MINGKUN</creatorcontrib><creatorcontrib>LIU YIN</creatorcontrib><creatorcontrib>LYU PENGWEI</creatorcontrib><creatorcontrib>SHI YAOXIN</creatorcontrib><creatorcontrib>WU HANXIAO</creatorcontrib><title>One-rocket multi-satellite layout method and system based on separation safety design</title><description>The invention relates to a one-rocket multi-satellite layout method and system based on separation safety design, and the method comprises the steps: obtaining the orbit injection attitude deviation at a satellite-rocket separation moment, and setting an initial separation state; setting mass center coordinates of M groups of satellites relative to a rocket body and separation energy of the satellites in an initial separation state, and completing population initialization; establishing a fitness function by taking the minimum far-field distance of the two satellites from the half period to the five periods after separation and the sum of the attitude angular velocities of the satellites after separation as optimization indexes; calculating a fitness function value of each particle; updating an individual extreme value and a global extreme value; updating the particle speed and the particle position; and when a preset ending condition is met, outputting a one-rocket multi-satellite layout optimization result.</description><subject>CALCULATING</subject><subject>COMPUTING</subject><subject>COUNTING</subject><subject>ELECTRIC DIGITAL DATA PROCESSING</subject><subject>PHYSICS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2024</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNirEKwkAQBa-xEPUf1g84MCZoLUGx0kbrsOZe4uHlLmQ3Rf5eBT_AaoZh5uZ-jbBDql9Q6sag3gorQvAKCjyl8ZOhz-SIoyOZRNHRgwWOUiRBzwOr_yo30IkcxLdxaWYNB8Hqx4VZn4638mzRpwrSc40IrcpLlu13ebHZFof8n-cNBPY5eQ</recordid><startdate>20240301</startdate><enddate>20240301</enddate><creator>ZHAO WEN</creator><creator>CHEN SHIQIANG</creator><creator>ZHANG RAN</creator><creator>XU SHANSHU</creator><creator>LI JINGLIN</creator><creator>LI JUN</creator><creator>GU MINGKUN</creator><creator>LIU YIN</creator><creator>LYU PENGWEI</creator><creator>SHI YAOXIN</creator><creator>WU HANXIAO</creator><scope>EVB</scope></search><sort><creationdate>20240301</creationdate><title>One-rocket multi-satellite layout method and system based on separation safety design</title><author>ZHAO WEN ; CHEN SHIQIANG ; ZHANG RAN ; XU SHANSHU ; LI JINGLIN ; LI JUN ; GU MINGKUN ; LIU YIN ; LYU PENGWEI ; SHI YAOXIN ; WU HANXIAO</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN117634024A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2024</creationdate><topic>CALCULATING</topic><topic>COMPUTING</topic><topic>COUNTING</topic><topic>ELECTRIC DIGITAL DATA PROCESSING</topic><topic>PHYSICS</topic><toplevel>online_resources</toplevel><creatorcontrib>ZHAO WEN</creatorcontrib><creatorcontrib>CHEN SHIQIANG</creatorcontrib><creatorcontrib>ZHANG RAN</creatorcontrib><creatorcontrib>XU SHANSHU</creatorcontrib><creatorcontrib>LI JINGLIN</creatorcontrib><creatorcontrib>LI JUN</creatorcontrib><creatorcontrib>GU MINGKUN</creatorcontrib><creatorcontrib>LIU YIN</creatorcontrib><creatorcontrib>LYU PENGWEI</creatorcontrib><creatorcontrib>SHI YAOXIN</creatorcontrib><creatorcontrib>WU HANXIAO</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>ZHAO WEN</au><au>CHEN SHIQIANG</au><au>ZHANG RAN</au><au>XU SHANSHU</au><au>LI JINGLIN</au><au>LI JUN</au><au>GU MINGKUN</au><au>LIU YIN</au><au>LYU PENGWEI</au><au>SHI YAOXIN</au><au>WU HANXIAO</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>One-rocket multi-satellite layout method and system based on separation safety design</title><date>2024-03-01</date><risdate>2024</risdate><abstract>The invention relates to a one-rocket multi-satellite layout method and system based on separation safety design, and the method comprises the steps: obtaining the orbit injection attitude deviation at a satellite-rocket separation moment, and setting an initial separation state; setting mass center coordinates of M groups of satellites relative to a rocket body and separation energy of the satellites in an initial separation state, and completing population initialization; establishing a fitness function by taking the minimum far-field distance of the two satellites from the half period to the five periods after separation and the sum of the attitude angular velocities of the satellites after separation as optimization indexes; calculating a fitness function value of each particle; updating an individual extreme value and a global extreme value; updating the particle speed and the particle position; and when a preset ending condition is met, outputting a one-rocket multi-satellite layout optimization result.</abstract><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | chi ; eng |
| recordid | cdi_epo_espacenet_CN117634024A |
| source | esp@cenet |
| subjects | CALCULATING COMPUTING COUNTING ELECTRIC DIGITAL DATA PROCESSING PHYSICS |
| title | One-rocket multi-satellite layout method and system based on separation safety design |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-23T13%3A47%3A56IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-epo_EVB&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=ZHAO%20WEN&rft.date=2024-03-01&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3ECN117634024A%3C/epo_EVB%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |