Missile-borne platform navigation method and system
The invention provides a missile-borne platform navigation method and system. The missile-borne platform navigation method comprises the following steps: acquiring an output state value at the current moment through an inertial navigation device; inquiring a map landmark at the current moment, and c...
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| creator | HE ZHANGMING LYU DONGHUI WANG JIONGQI CHEN YUYUN HOU BOWEN WEI JUHUI ZHOU XUANYING |
| description | The invention provides a missile-borne platform navigation method and system. The missile-borne platform navigation method comprises the following steps: acquiring an output state value at the current moment through an inertial navigation device; inquiring a map landmark at the current moment, and calculating an output deviation estimation value based on the map landmark at the current moment according to the inquired map landmark at the current moment; inquiring the opportunity landmark at the current moment, and calculating an output deviation estimation value based on the opportunity landmark at the current moment according to the inquired opportunity landmark at the current moment; carrying out fusion calculation on the output deviation estimation value based on the map landmark and the output deviation estimation value based on the opportunity landmark to obtain an output deviation compensation item at the current moment; and substituting the output deviation compensation item into the output state value |
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The missile-borne platform navigation method comprises the following steps: acquiring an output state value at the current moment through an inertial navigation device; inquiring a map landmark at the current moment, and calculating an output deviation estimation value based on the map landmark at the current moment according to the inquired map landmark at the current moment; inquiring the opportunity landmark at the current moment, and calculating an output deviation estimation value based on the opportunity landmark at the current moment according to the inquired opportunity landmark at the current moment; carrying out fusion calculation on the output deviation estimation value based on the map landmark and the output deviation estimation value based on the opportunity landmark to obtain an output deviation compensation item at the current moment; and substituting the output deviation compensation item into the output state value</description><language>chi ; eng</language><subject>GYROSCOPIC INSTRUMENTS ; MEASURING ; MEASURING DISTANCES, LEVELS OR BEARINGS ; NAVIGATION ; PHOTOGRAMMETRY OR VIDEOGRAMMETRY ; PHYSICS ; SURVEYING ; TESTING</subject><creationdate>2021</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=20210604&DB=EPODOC&CC=CN&NR=112902957A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20210604&DB=EPODOC&CC=CN&NR=112902957A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>HE ZHANGMING</creatorcontrib><creatorcontrib>LYU DONGHUI</creatorcontrib><creatorcontrib>WANG JIONGQI</creatorcontrib><creatorcontrib>CHEN YUYUN</creatorcontrib><creatorcontrib>HOU BOWEN</creatorcontrib><creatorcontrib>WEI JUHUI</creatorcontrib><creatorcontrib>ZHOU XUANYING</creatorcontrib><title>Missile-borne platform navigation method and system</title><description>The invention provides a missile-borne platform navigation method and system. 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The missile-borne platform navigation method comprises the following steps: acquiring an output state value at the current moment through an inertial navigation device; inquiring a map landmark at the current moment, and calculating an output deviation estimation value based on the map landmark at the current moment according to the inquired map landmark at the current moment; inquiring the opportunity landmark at the current moment, and calculating an output deviation estimation value based on the opportunity landmark at the current moment according to the inquired opportunity landmark at the current moment; carrying out fusion calculation on the output deviation estimation value based on the map landmark and the output deviation estimation value based on the opportunity landmark to obtain an output deviation compensation item at the current moment; and substituting the output deviation compensation item into the output state value</abstract><oa>free_for_read</oa></addata></record> |
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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 | Missile-borne platform navigation method and system |
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