Design of Vertical Launch Control System for Antiaircraft Missile Using Optical Control
Vertical launching technology can effectively improve the performance of antiaircraft missile, which can reduce the preparative time for antiaircraft missile to attack the targets. The scheme of vertical launching control system is present. The autopilot of missile has used the angle of pitch, yaw a...
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| creator | Zhang, Hong-yan Li, Fang-xi Fan, Yong-hua |
| description | Vertical launching technology can effectively improve the performance of antiaircraft missile, which can reduce the preparative time for antiaircraft missile to attack the targets. The scheme of vertical launching control system is present. The autopilot of missile has used the angle of pitch, yaw and roll as the feedback signal. The missile can flight to any direction from the vertical launching state by controlling the Euler angle of the missile. The model of the antiaircraft missile which has used multiple controls of aerodynamic actuator and TVC (thrust vector control) is given, and then the flight control system has been designed by using linear quadratic regulator (LQR) theory. Finally it is proved by simulation that the performance of the vertical launching control system can meet the requirement and the scheme of the control system is feasible. |
| doi_str_mv | 10.1109/ICMTMA.2010.264 |
| format | Conference Proceeding |
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The scheme of vertical launching control system is present. The autopilot of missile has used the angle of pitch, yaw and roll as the feedback signal. The missile can flight to any direction from the vertical launching state by controlling the Euler angle of the missile. The model of the antiaircraft missile which has used multiple controls of aerodynamic actuator and TVC (thrust vector control) is given, and then the flight control system has been designed by using linear quadratic regulator (LQR) theory. Finally it is proved by simulation that the performance of the vertical launching control system can meet the requirement and the scheme of the control system is feasible.</description><identifier>ISSN: 2157-1473</identifier><identifier>ISBN: 1424450012</identifier><identifier>ISBN: 9781424450015</identifier><identifier>EISBN: 9781424457397</identifier><identifier>EISBN: 1424457394</identifier><identifier>DOI: 10.1109/ICMTMA.2010.264</identifier><identifier>LCCN: 2009943962</identifier><language>eng ; jpn</language><publisher>IEEE</publisher><subject>Aerodynamics ; Aerospace control ; Antiaircraft Missile ; Control system synthesis ; Control systems ; Hydraulic actuators ; Linear Quadratic Regulator ; Missiles ; Optical control ; Optical design ; Optical feedback ; Regulators ; Thrust Vector/Aerodynamic ; Vertical Launch</subject><ispartof>2010 International Conference on Measuring Technology and Mechatronics Automation, 2010, Vol.1, p.1068-1071</ispartof><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://ieeexplore.ieee.org/document/5459696$$EHTML$$P50$$Gieee$$H</linktohtml><link.rule.ids>309,310,777,781,786,787,2052,27906,54901</link.rule.ids><linktorsrc>$$Uhttps://ieeexplore.ieee.org/document/5459696$$EView_record_in_IEEE$$FView_record_in_$$GIEEE</linktorsrc></links><search><creatorcontrib>Zhang, Hong-yan</creatorcontrib><creatorcontrib>Li, Fang-xi</creatorcontrib><creatorcontrib>Fan, Yong-hua</creatorcontrib><title>Design of Vertical Launch Control System for Antiaircraft Missile Using Optical Control</title><title>2010 International Conference on Measuring Technology and Mechatronics Automation</title><addtitle>ICMTMA</addtitle><description>Vertical launching technology can effectively improve the performance of antiaircraft missile, which can reduce the preparative time for antiaircraft missile to attack the targets. The scheme of vertical launching control system is present. The autopilot of missile has used the angle of pitch, yaw and roll as the feedback signal. The missile can flight to any direction from the vertical launching state by controlling the Euler angle of the missile. The model of the antiaircraft missile which has used multiple controls of aerodynamic actuator and TVC (thrust vector control) is given, and then the flight control system has been designed by using linear quadratic regulator (LQR) theory. Finally it is proved by simulation that the performance of the vertical launching control system can meet the requirement and the scheme of the control system is feasible.</description><subject>Aerodynamics</subject><subject>Aerospace control</subject><subject>Antiaircraft Missile</subject><subject>Control system synthesis</subject><subject>Control systems</subject><subject>Hydraulic actuators</subject><subject>Linear Quadratic Regulator</subject><subject>Missiles</subject><subject>Optical control</subject><subject>Optical design</subject><subject>Optical feedback</subject><subject>Regulators</subject><subject>Thrust Vector/Aerodynamic</subject><subject>Vertical Launch</subject><issn>2157-1473</issn><isbn>1424450012</isbn><isbn>9781424450015</isbn><isbn>9781424457397</isbn><isbn>1424457394</isbn><fulltext>true</fulltext><rsrctype>conference_proceeding</rsrctype><creationdate>2010</creationdate><recordtype>conference_proceeding</recordtype><sourceid>6IE</sourceid><sourceid>RIE</sourceid><recordid>eNotjM1OwkAYRccoiYCsXbiZFyh-899ZkvpHUsJC0CWZab_BMaUlnbrg7dXA6ubek3MJuWcwZwzs47JYbVaLOYe_gWt5RWbW5ExyKZUR1lyTybkAMH5DxpwpkzFpxIhMOIC1UljNb8kspW8AECzPreFj8vmEKe5b2gX6gf0QK9fQ0v201Rctunbou4a-n9KABxq6ni7aIbrYV70LA13FlGKDdJtiu6fr41m-WHdkFFyTcHbJKdm-PG-Kt6xcvy6LRZlFpvSQ8RDACV0LlzMUPnghJXrpZVAV-hr_acUFrz0o6zWgMDXXIWgeQOYSxZQ8nH8jIu6OfTy4_rRTUllttfgFl8BXVQ</recordid><startdate>201003</startdate><enddate>201003</enddate><creator>Zhang, Hong-yan</creator><creator>Li, Fang-xi</creator><creator>Fan, Yong-hua</creator><general>IEEE</general><scope>6IE</scope><scope>6IL</scope><scope>CBEJK</scope><scope>RIE</scope><scope>RIL</scope></search><sort><creationdate>201003</creationdate><title>Design of Vertical Launch Control System for Antiaircraft Missile Using Optical Control</title><author>Zhang, Hong-yan ; Li, Fang-xi ; Fan, Yong-hua</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-i156t-2ff0a36d3a81e3bfb344eb4b4f5cebdef0a3c232db059b60e37d26ff62f0484e3</frbrgroupid><rsrctype>conference_proceedings</rsrctype><prefilter>conference_proceedings</prefilter><language>eng ; jpn</language><creationdate>2010</creationdate><topic>Aerodynamics</topic><topic>Aerospace control</topic><topic>Antiaircraft Missile</topic><topic>Control system synthesis</topic><topic>Control systems</topic><topic>Hydraulic actuators</topic><topic>Linear Quadratic Regulator</topic><topic>Missiles</topic><topic>Optical control</topic><topic>Optical design</topic><topic>Optical feedback</topic><topic>Regulators</topic><topic>Thrust Vector/Aerodynamic</topic><topic>Vertical Launch</topic><toplevel>online_resources</toplevel><creatorcontrib>Zhang, Hong-yan</creatorcontrib><creatorcontrib>Li, Fang-xi</creatorcontrib><creatorcontrib>Fan, Yong-hua</creatorcontrib><collection>IEEE Electronic Library (IEL) Conference Proceedings</collection><collection>IEEE Proceedings Order Plan All Online (POP All Online) 1998-present by volume</collection><collection>IEEE Xplore All Conference Proceedings</collection><collection>IEEE Electronic Library (IEL)</collection><collection>IEEE Proceedings Order Plans (POP All) 1998-Present</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Zhang, Hong-yan</au><au>Li, Fang-xi</au><au>Fan, Yong-hua</au><format>book</format><genre>proceeding</genre><ristype>CONF</ristype><atitle>Design of Vertical Launch Control System for Antiaircraft Missile Using Optical Control</atitle><btitle>2010 International Conference on Measuring Technology and Mechatronics Automation</btitle><stitle>ICMTMA</stitle><date>2010-03</date><risdate>2010</risdate><volume>1</volume><spage>1068</spage><epage>1071</epage><pages>1068-1071</pages><issn>2157-1473</issn><isbn>1424450012</isbn><isbn>9781424450015</isbn><eisbn>9781424457397</eisbn><eisbn>1424457394</eisbn><abstract>Vertical launching technology can effectively improve the performance of antiaircraft missile, which can reduce the preparative time for antiaircraft missile to attack the targets. The scheme of vertical launching control system is present. The autopilot of missile has used the angle of pitch, yaw and roll as the feedback signal. The missile can flight to any direction from the vertical launching state by controlling the Euler angle of the missile. The model of the antiaircraft missile which has used multiple controls of aerodynamic actuator and TVC (thrust vector control) is given, and then the flight control system has been designed by using linear quadratic regulator (LQR) theory. Finally it is proved by simulation that the performance of the vertical launching control system can meet the requirement and the scheme of the control system is feasible.</abstract><pub>IEEE</pub><doi>10.1109/ICMTMA.2010.264</doi><tpages>4</tpages></addata></record> |
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| ispartof | 2010 International Conference on Measuring Technology and Mechatronics Automation, 2010, Vol.1, p.1068-1071 |
| issn | 2157-1473 |
| language | eng ; jpn |
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| source | IEEE Electronic Library (IEL) Conference Proceedings |
| subjects | Aerodynamics Aerospace control Antiaircraft Missile Control system synthesis Control systems Hydraulic actuators Linear Quadratic Regulator Missiles Optical control Optical design Optical feedback Regulators Thrust Vector/Aerodynamic Vertical Launch |
| title | Design of Vertical Launch Control System for Antiaircraft Missile Using Optical Control |
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