Attitude and orbit control semi-physical simulation method and system for satellite constellation

Attitude and orbit control semi-physical simulation method and system for satellite constellation

The invention provides an attitude and orbit control semi-physical simulation method and simulation system for a satellite constellation. The satellite constellation comprises a plurality of satellites, each satellite comprises at least one attitude sensor and at least one execution mechanism, and t...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: XIE XIANGHUA, YANG GUANG, YANG WENZHE, YAN LINGLING, DAI ZHENGSHENG, BIAN JING, ZHU YE, HUANG ZHIWEI, HE XIAWEI
Format: Patent
Sprache:chi ; eng
Schlagworte:
CONTROL OR REGULATING SYSTEMS IN GENERAL
CONTROLLING
FUNCTIONAL ELEMENTS OF SUCH SYSTEMS
MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS ORELEMENTS
PHYSICS
REGULATING
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 XIE XIANGHUA
YANG GUANG
YANG WENZHE
YAN LINGLING
DAI ZHENGSHENG
BIAN JING
ZHU YE
HUANG ZHIWEI
HE XIAWEI
description The invention provides an attitude and orbit control semi-physical simulation method and simulation system for a satellite constellation. The satellite constellation comprises a plurality of satellites, each satellite comprises at least one attitude sensor and at least one execution mechanism, and the simulation method comprises the steps that attitude and orbit control dynamics mathematical models corresponding to the satellites are established, and the attitude and orbit control dynamics mathematical models are in one-to-one correspondence with the satellites; an interface module is established, and the interface module is used for obtaining an execution mechanism instruction from each satellite and sending the execution mechanism instruction to the attitude and orbit control dynamics mathematical model corresponding to each satellite; and the attitude and orbit control dynamics mathematical model calculates sensor data and execution mechanism data of the satellites according to the execution mechanism inst
format Patent
fullrecord <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_CN114967496A</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>CN114967496A</sourcerecordid><originalsourceid>FETCH-epo_espacenet_CN114967496A3</originalsourceid><addsrcrecordid>eNqNjLEKwkAQRNNYiPoP6wekCIpiGYJiZWUf1rsNWbi7DbebIn9vEvwAi2Fm4M1sC6zN2EZPgMmD5A8bOEmWJYBS5HLoJ2WHc-M4BjSWBJGsF78udFKjCJ1kUDQKgY2WA13ySu-LTYdB6fDzXXF83N_Ns6RBWtIBHSWytnlV1fl2uc6qT_8wX38fPsE</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Attitude and orbit control semi-physical simulation method and system for satellite constellation</title><source>esp@cenet</source><creator>XIE XIANGHUA ; YANG GUANG ; YANG WENZHE ; YAN LINGLING ; DAI ZHENGSHENG ; BIAN JING ; ZHU YE ; HUANG ZHIWEI ; HE XIAWEI</creator><creatorcontrib>XIE XIANGHUA ; YANG GUANG ; YANG WENZHE ; YAN LINGLING ; DAI ZHENGSHENG ; BIAN JING ; ZHU YE ; HUANG ZHIWEI ; HE XIAWEI</creatorcontrib><description>The invention provides an attitude and orbit control semi-physical simulation method and simulation system for a satellite constellation. The satellite constellation comprises a plurality of satellites, each satellite comprises at least one attitude sensor and at least one execution mechanism, and the simulation method comprises the steps that attitude and orbit control dynamics mathematical models corresponding to the satellites are established, and the attitude and orbit control dynamics mathematical models are in one-to-one correspondence with the satellites; an interface module is established, and the interface module is used for obtaining an execution mechanism instruction from each satellite and sending the execution mechanism instruction to the attitude and orbit control dynamics mathematical model corresponding to each satellite; and the attitude and orbit control dynamics mathematical model calculates sensor data and execution mechanism data of the satellites according to the execution mechanism inst</description><language>chi ; eng</language><subject>CONTROL OR REGULATING SYSTEMS IN GENERAL ; CONTROLLING ; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS ; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS ORELEMENTS ; PHYSICS ; REGULATING</subject><creationdate>2022</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&amp;date=20220830&amp;DB=EPODOC&amp;CC=CN&amp;NR=114967496A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,778,883,25551,76302</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&amp;date=20220830&amp;DB=EPODOC&amp;CC=CN&amp;NR=114967496A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>XIE XIANGHUA</creatorcontrib><creatorcontrib>YANG GUANG</creatorcontrib><creatorcontrib>YANG WENZHE</creatorcontrib><creatorcontrib>YAN LINGLING</creatorcontrib><creatorcontrib>DAI ZHENGSHENG</creatorcontrib><creatorcontrib>BIAN JING</creatorcontrib><creatorcontrib>ZHU YE</creatorcontrib><creatorcontrib>HUANG ZHIWEI</creatorcontrib><creatorcontrib>HE XIAWEI</creatorcontrib><title>Attitude and orbit control semi-physical simulation method and system for satellite constellation</title><description>The invention provides an attitude and orbit control semi-physical simulation method and simulation system for a satellite constellation. The satellite constellation comprises a plurality of satellites, each satellite comprises at least one attitude sensor and at least one execution mechanism, and the simulation method comprises the steps that attitude and orbit control dynamics mathematical models corresponding to the satellites are established, and the attitude and orbit control dynamics mathematical models are in one-to-one correspondence with the satellites; an interface module is established, and the interface module is used for obtaining an execution mechanism instruction from each satellite and sending the execution mechanism instruction to the attitude and orbit control dynamics mathematical model corresponding to each satellite; and the attitude and orbit control dynamics mathematical model calculates sensor data and execution mechanism data of the satellites according to the execution mechanism inst</description><subject>CONTROL OR REGULATING SYSTEMS IN GENERAL</subject><subject>CONTROLLING</subject><subject>FUNCTIONAL ELEMENTS OF SUCH SYSTEMS</subject><subject>MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS ORELEMENTS</subject><subject>PHYSICS</subject><subject>REGULATING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2022</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNjLEKwkAQRNNYiPoP6wekCIpiGYJiZWUf1rsNWbi7DbebIn9vEvwAi2Fm4M1sC6zN2EZPgMmD5A8bOEmWJYBS5HLoJ2WHc-M4BjSWBJGsF78udFKjCJ1kUDQKgY2WA13ySu-LTYdB6fDzXXF83N_Ns6RBWtIBHSWytnlV1fl2uc6qT_8wX38fPsE</recordid><startdate>20220830</startdate><enddate>20220830</enddate><creator>XIE XIANGHUA</creator><creator>YANG GUANG</creator><creator>YANG WENZHE</creator><creator>YAN LINGLING</creator><creator>DAI ZHENGSHENG</creator><creator>BIAN JING</creator><creator>ZHU YE</creator><creator>HUANG ZHIWEI</creator><creator>HE XIAWEI</creator><scope>EVB</scope></search><sort><creationdate>20220830</creationdate><title>Attitude and orbit control semi-physical simulation method and system for satellite constellation</title><author>XIE XIANGHUA ; YANG GUANG ; YANG WENZHE ; YAN LINGLING ; DAI ZHENGSHENG ; BIAN JING ; ZHU YE ; HUANG ZHIWEI ; HE XIAWEI</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN114967496A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2022</creationdate><topic>CONTROL OR REGULATING SYSTEMS IN GENERAL</topic><topic>CONTROLLING</topic><topic>FUNCTIONAL ELEMENTS OF SUCH SYSTEMS</topic><topic>MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS ORELEMENTS</topic><topic>PHYSICS</topic><topic>REGULATING</topic><toplevel>online_resources</toplevel><creatorcontrib>XIE XIANGHUA</creatorcontrib><creatorcontrib>YANG GUANG</creatorcontrib><creatorcontrib>YANG WENZHE</creatorcontrib><creatorcontrib>YAN LINGLING</creatorcontrib><creatorcontrib>DAI ZHENGSHENG</creatorcontrib><creatorcontrib>BIAN JING</creatorcontrib><creatorcontrib>ZHU YE</creatorcontrib><creatorcontrib>HUANG ZHIWEI</creatorcontrib><creatorcontrib>HE XIAWEI</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>XIE XIANGHUA</au><au>YANG GUANG</au><au>YANG WENZHE</au><au>YAN LINGLING</au><au>DAI ZHENGSHENG</au><au>BIAN JING</au><au>ZHU YE</au><au>HUANG ZHIWEI</au><au>HE XIAWEI</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Attitude and orbit control semi-physical simulation method and system for satellite constellation</title><date>2022-08-30</date><risdate>2022</risdate><abstract>The invention provides an attitude and orbit control semi-physical simulation method and simulation system for a satellite constellation. The satellite constellation comprises a plurality of satellites, each satellite comprises at least one attitude sensor and at least one execution mechanism, and the simulation method comprises the steps that attitude and orbit control dynamics mathematical models corresponding to the satellites are established, and the attitude and orbit control dynamics mathematical models are in one-to-one correspondence with the satellites; an interface module is established, and the interface module is used for obtaining an execution mechanism instruction from each satellite and sending the execution mechanism instruction to the attitude and orbit control dynamics mathematical model corresponding to each satellite; and the attitude and orbit control dynamics mathematical model calculates sensor data and execution mechanism data of the satellites according to the execution mechanism inst</abstract><oa>free_for_read</oa></addata></record>
fulltext fulltext_linktorsrc
identifier
ispartof
issn
language chi ; eng
recordid cdi_epo_espacenet_CN114967496A
source esp@cenet
subjects CONTROL OR REGULATING SYSTEMS IN GENERAL
CONTROLLING
FUNCTIONAL ELEMENTS OF SUCH SYSTEMS
MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS ORELEMENTS
PHYSICS
REGULATING
title Attitude and orbit control semi-physical simulation method and system for satellite constellation
url https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-15T18%3A47%3A42IST&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=XIE%20XIANGHUA&rft.date=2022-08-30&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3ECN114967496A%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