Inertial-navigation quick and initial alignment method under robust optimal significance
The invention discloses an inertial-navigation quick and initial alignment method under robust optimal significance, comprising the following steps of: introducing an auxiliary matrix and an auxiliary feedback control vector into an initial alignment system; solving a robust optimal control problem...
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| creator | DAI SHAOZHONG WU GUANGYUE YUE DONGXUE |
| description | The invention discloses an inertial-navigation quick and initial alignment method under robust optimal significance, comprising the following steps of: introducing an auxiliary matrix and an auxiliary feedback control vector into an initial alignment system; solving a robust optimal control problem according to a maxmin index, determining a state feedback control matrix; and in an initial alignment process, recursively calculating a state vector in an error equation of an inertial-navigation system in real time by using an improved H infinite filter, forming a closed loop after feedback, and obtaining three misalignment angles after converging the system. The inertial-navigation quick and initial alignment method has good system structure and good stable parameter robustness, improves dynamic responding quality and increases the initial alignment rapidity of the initial alignment system. |
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The inertial-navigation quick and initial alignment method has good system structure and good stable parameter robustness, improves dynamic responding quality and increases the initial alignment rapidity of the initial alignment system.</description><language>chi ; eng</language><subject>GYROSCOPIC INSTRUMENTS ; MEASURING ; MEASURING DISTANCES, LEVELS OR BEARINGS ; NAVIGATION ; PHOTOGRAMMETRY OR VIDEOGRAMMETRY ; PHYSICS ; SURVEYING ; TESTING</subject><creationdate>2011</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=20110427&DB=EPODOC&CC=CN&NR=102032922A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20110427&DB=EPODOC&CC=CN&NR=102032922A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>DAI SHAOZHONG</creatorcontrib><creatorcontrib>WU GUANGYUE</creatorcontrib><creatorcontrib>YUE DONGXUE</creatorcontrib><title>Inertial-navigation quick and initial alignment method under robust optimal significance</title><description>The invention discloses an inertial-navigation quick and initial alignment method under robust optimal significance, comprising the following steps of: introducing an auxiliary matrix and an auxiliary feedback control vector into an initial alignment system; solving a robust optimal control problem according to a maxmin index, determining a state feedback control matrix; and in an initial alignment process, recursively calculating a state vector in an error equation of an inertial-navigation system in real time by using an improved H infinite filter, forming a closed loop after feedback, and obtaining three misalignment angles after converging the system. The inertial-navigation quick and initial alignment method has good system structure and good stable parameter robustness, improves dynamic responding quality and increases the initial alignment rapidity of the initial alignment system.</description><subject>GYROSCOPIC INSTRUMENTS</subject><subject>MEASURING</subject><subject>MEASURING DISTANCES, LEVELS OR BEARINGS</subject><subject>NAVIGATION</subject><subject>PHOTOGRAMMETRY OR VIDEOGRAMMETRY</subject><subject>PHYSICS</subject><subject>SURVEYING</subject><subject>TESTING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2011</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNyjEOwjAMQNEuDAi4gzlApZJOjKgCwcLEwFaZxG0tWickDuenSByA6Q__LYv7RSgq41gKvrlHZS_wymyfgOKAhb8TcOReJhKFiXTwDrI4ihD9IycFH5SnWaUZcccWxdK6WHQ4Jtr8uiq2p-OtOZcUfEspoCUhbZvrrjJVbfbGHOp_zAf55Tru</recordid><startdate>20110427</startdate><enddate>20110427</enddate><creator>DAI SHAOZHONG</creator><creator>WU GUANGYUE</creator><creator>YUE DONGXUE</creator><scope>EVB</scope></search><sort><creationdate>20110427</creationdate><title>Inertial-navigation quick and initial alignment method under robust optimal significance</title><author>DAI SHAOZHONG ; WU GUANGYUE ; YUE DONGXUE</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN102032922A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2011</creationdate><topic>GYROSCOPIC INSTRUMENTS</topic><topic>MEASURING</topic><topic>MEASURING DISTANCES, LEVELS OR BEARINGS</topic><topic>NAVIGATION</topic><topic>PHOTOGRAMMETRY OR VIDEOGRAMMETRY</topic><topic>PHYSICS</topic><topic>SURVEYING</topic><topic>TESTING</topic><toplevel>online_resources</toplevel><creatorcontrib>DAI SHAOZHONG</creatorcontrib><creatorcontrib>WU GUANGYUE</creatorcontrib><creatorcontrib>YUE DONGXUE</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>DAI SHAOZHONG</au><au>WU GUANGYUE</au><au>YUE DONGXUE</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Inertial-navigation quick and initial alignment method under robust optimal significance</title><date>2011-04-27</date><risdate>2011</risdate><abstract>The invention discloses an inertial-navigation quick and initial alignment method under robust optimal significance, comprising the following steps of: introducing an auxiliary matrix and an auxiliary feedback control vector into an initial alignment system; solving a robust optimal control problem according to a maxmin index, determining a state feedback control matrix; and in an initial alignment process, recursively calculating a state vector in an error equation of an inertial-navigation system in real time by using an improved H infinite filter, forming a closed loop after feedback, and obtaining three misalignment angles after converging the system. 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| language | chi ; eng |
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| subjects | GYROSCOPIC INSTRUMENTS MEASURING MEASURING DISTANCES, LEVELS OR BEARINGS NAVIGATION PHOTOGRAMMETRY OR VIDEOGRAMMETRY PHYSICS SURVEYING TESTING |
| title | Inertial-navigation quick and initial alignment method under robust optimal significance |
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