Aircraft guidance system and method for realizing fall angle constraint
The invention discloses an aircraft guidance system and method for realizing fall angle constraint. The system can firstly set a launching angle of an aircraft by inputting an expected fall angle and a target distance coordinate; a missile-target sight angle of the aircraft in real time is measured...
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| creator | WANG WEI WANG WEIBIN NAN YUXIANG HU KUANRONG LIU JIAQI WANG LUQIANG |
| description | The invention discloses an aircraft guidance system and method for realizing fall angle constraint. The system can firstly set a launching angle of an aircraft by inputting an expected fall angle and a target distance coordinate; a missile-target sight angle of the aircraft in real time is measured through a missile-target sight angle measuring module after the aircraft is started and controlled, and the measured missile-target sight angle is transmitted to a guidance law resolving module in real time; the guidance law resolving module is used for resolving a guidance law in real time according to the measured missile-target sight angle after the aircraft is started and controlled, and transmitting the resolved guidance law information to an execution module in real time; and the execution module can control the aircraft to move according to the calculated guidance law information, so that the falling angle constraint of the aircraft is realized.
本发明公开了一种实现落角约束的飞行器制导系统和方法，该系统可以首先可以通过输入期望落角和目标距离坐标，设定飞行器的发射角；通过 |
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本发明公开了一种实现落角约束的飞行器制导系统和方法，该系统可以首先可以通过输入期望落角和目标距离坐标，设定飞行器的发射角；通过</description><language>chi ; eng</language><subject>AIMING ; AMMUNITION ; BLASTING ; EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION ; HEATING ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPON SIGHTS ; WEAPONS</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=20211012&DB=EPODOC&CC=CN&NR=113494869A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25562,76317</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20211012&DB=EPODOC&CC=CN&NR=113494869A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>WANG WEI</creatorcontrib><creatorcontrib>WANG WEIBIN</creatorcontrib><creatorcontrib>NAN YUXIANG</creatorcontrib><creatorcontrib>HU KUANRONG</creatorcontrib><creatorcontrib>LIU JIAQI</creatorcontrib><creatorcontrib>WANG LUQIANG</creatorcontrib><title>Aircraft guidance system and method for realizing fall angle constraint</title><description>The invention discloses an aircraft guidance system and method for realizing fall angle constraint. The system can firstly set a launching angle of an aircraft by inputting an expected fall angle and a target distance coordinate; a missile-target sight angle of the aircraft in real time is measured through a missile-target sight angle measuring module after the aircraft is started and controlled, and the measured missile-target sight angle is transmitted to a guidance law resolving module in real time; the guidance law resolving module is used for resolving a guidance law in real time according to the measured missile-target sight angle after the aircraft is started and controlled, and transmitting the resolved guidance law information to an execution module in real time; and the execution module can control the aircraft to move according to the calculated guidance law information, so that the falling angle constraint of the aircraft is realized.
本发明公开了一种实现落角约束的飞行器制导系统和方法，该系统可以首先可以通过输入期望落角和目标距离坐标，设定飞行器的发射角；通过</description><subject>AIMING</subject><subject>AMMUNITION</subject><subject>BLASTING</subject><subject>EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION</subject><subject>HEATING</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>WEAPON SIGHTS</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2021</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZHB3zCxKLkpMK1FIL81MScxLTlUoriwuSc1VSMxLUchNLcnIT1FIyy9SKEpNzMmsysxLV0hLzMkByqbnpCok5-cVlxQlZuaV8DCwAsWLU3mhNDeDoptriLOHbmpBfnxqcUFicmpeakm8s5-hobGJpYmFmaWjMTFqAHPTNCQ</recordid><startdate>20211012</startdate><enddate>20211012</enddate><creator>WANG WEI</creator><creator>WANG WEIBIN</creator><creator>NAN YUXIANG</creator><creator>HU KUANRONG</creator><creator>LIU JIAQI</creator><creator>WANG LUQIANG</creator><scope>EVB</scope></search><sort><creationdate>20211012</creationdate><title>Aircraft guidance system and method for realizing fall angle constraint</title><author>WANG WEI ; WANG WEIBIN ; NAN YUXIANG ; HU KUANRONG ; LIU JIAQI ; WANG LUQIANG</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN113494869A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2021</creationdate><topic>AIMING</topic><topic>AMMUNITION</topic><topic>BLASTING</topic><topic>EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION</topic><topic>HEATING</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPON SIGHTS</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>WANG WEI</creatorcontrib><creatorcontrib>WANG WEIBIN</creatorcontrib><creatorcontrib>NAN YUXIANG</creatorcontrib><creatorcontrib>HU KUANRONG</creatorcontrib><creatorcontrib>LIU JIAQI</creatorcontrib><creatorcontrib>WANG LUQIANG</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>WANG WEI</au><au>WANG WEIBIN</au><au>NAN YUXIANG</au><au>HU KUANRONG</au><au>LIU JIAQI</au><au>WANG LUQIANG</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Aircraft guidance system and method for realizing fall angle constraint</title><date>2021-10-12</date><risdate>2021</risdate><abstract>The invention discloses an aircraft guidance system and method for realizing fall angle constraint. The system can firstly set a launching angle of an aircraft by inputting an expected fall angle and a target distance coordinate; a missile-target sight angle of the aircraft in real time is measured through a missile-target sight angle measuring module after the aircraft is started and controlled, and the measured missile-target sight angle is transmitted to a guidance law resolving module in real time; the guidance law resolving module is used for resolving a guidance law in real time according to the measured missile-target sight angle after the aircraft is started and controlled, and transmitting the resolved guidance law information to an execution module in real time; and the execution module can control the aircraft to move according to the calculated guidance law information, so that the falling angle constraint of the aircraft is realized.
本发明公开了一种实现落角约束的飞行器制导系统和方法，该系统可以首先可以通过输入期望落角和目标距离坐标，设定飞行器的发射角；通过</abstract><oa>free_for_read</oa></addata></record> |
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| language | chi ; eng |
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| subjects | AIMING AMMUNITION BLASTING EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION HEATING LIGHTING MECHANICAL ENGINEERING WEAPON SIGHTS WEAPONS |
| title | Aircraft guidance system and method for realizing fall angle constraint |
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