Sliding-Mode Guidance and Control for All-Aspect Interceptors with Terminal Angle Constraints
In this paper, sliding-mode-control-based guidance laws to intercept stationary, constant-velocity, and maneuvering targets at a desired impact angle are proposed. The desired impact angle, which is defined in terms of a desired line-of-sight angle, is achieved in finite time by selecting the missil...
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| Veröffentlicht in: | Journal of guidance, control, and dynamics control, and dynamics, 2012-07, Vol.35 (4), p.1230-1246 |
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| container_end_page | 1246 |
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| container_issue | 4 |
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| container_title | Journal of guidance, control, and dynamics |
| container_volume | 35 |
| creator | Kumar, Shashi Ranjan Rao, Sachit Ghose, Debasish |
| description | In this paper, sliding-mode-control-based guidance laws to intercept stationary, constant-velocity, and maneuvering targets at a desired impact angle are proposed. The desired impact angle, which is defined in terms of a desired line-of-sight angle, is achieved in finite time by selecting the missile's lateral acceleration to enforce terminal sliding mode on a switching surface designed using nonlinear engagement dynamics. The conditions for capturability are also presented. In addition, by considering a three-degree-of-freedom linear-interceptor dynamic model and by following the procedure used to design a dynamic sliding-mode controller, the interceptor autopilot is designed as a simple static controller to track the lateral acceleration generated by the guidance law. Numerical simulation results are presented to validate the proposed guidance laws and the autopilot design for different initial engagement geometries and impact angles. |
| doi_str_mv | 10.2514/1.55242 |
| format | Article |
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The desired impact angle, which is defined in terms of a desired line-of-sight angle, is achieved in finite time by selecting the missile's lateral acceleration to enforce terminal sliding mode on a switching surface designed using nonlinear engagement dynamics. The conditions for capturability are also presented. In addition, by considering a three-degree-of-freedom linear-interceptor dynamic model and by following the procedure used to design a dynamic sliding-mode controller, the interceptor autopilot is designed as a simple static controller to track the lateral acceleration generated by the guidance law. Numerical simulation results are presented to validate the proposed guidance laws and the autopilot design for different initial engagement geometries and impact angles.</description><identifier>ISSN: 0731-5090</identifier><identifier>EISSN: 1533-3884</identifier><identifier>DOI: 10.2514/1.55242</identifier><identifier>CODEN: JGCODS</identifier><language>eng</language><publisher>Reston, VA: American Institute of Aeronautics and Astronautics</publisher><subject>Acceleration ; Aerospace engineering ; Aircraft ; Angles (geometry) ; Applied sciences ; Automatic pilots ; Autopilots ; Computer science; control theory; systems ; Control system synthesis ; Control theory. 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Numerical simulation results are presented to validate the proposed guidance laws and the autopilot design for different initial engagement geometries and impact angles.</description><subject>Acceleration</subject><subject>Aerospace engineering</subject><subject>Aircraft</subject><subject>Angles (geometry)</subject><subject>Applied sciences</subject><subject>Automatic pilots</subject><subject>Autopilots</subject><subject>Computer science; control theory; systems</subject><subject>Control system synthesis</subject><subject>Control theory. Systems</subject><subject>Design</subject><subject>Exact sciences and technology</subject><subject>Impact angle</subject><subject>Interceptors</subject><subject>Laws</subject><subject>Missiles</subject><subject>Nonlinear dynamics</subject><subject>Terminals</subject><subject>Velocity</subject><issn>0731-5090</issn><issn>1533-3884</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2012</creationdate><recordtype>article</recordtype><recordid>eNqN0U1rFDEYB_AgFlxb8SsEVNTD1LxOMsdl0VqoeLAeZUgySU3JJmOSQf32Ztwi0gr1lEN--ed5AeApRqeEY_YGn3JOGHkANphT2lEp2UOwQYLijqMBPQKPS7lGCNMeiw348in4ycer7kOaLDxb_KSisVDFCe5SrDkF6FKG2xC6bZmtqfA8VpuNnWvKBX739Su8tHnvowpwG6-CXd-VmpWPtZyAI6dCsU9uzmPw-d3by9377uLj2flue9EpJmTtiCaDdIYZIm1vMdETV4i5iQrdO4YGzTVlVhNKNcVGaSQ144INsvVjyOToMXh1yJ1z-rbYUse9L8aGoKJNSxmx6AmmlFP8f5QMraD7KcNC9oMg7H6KqCR8kGylz27R67TkNr6mKOuFaFWu6uVBmZxKydaNc_Z7lX-2qHHd84jH33tu8sVNnipGBZfbAn35w0nfukF47eb5wSmv1F9_3ol7_U92uB7nyY1uCaHaH5X-Ashkvd0</recordid><startdate>20120701</startdate><enddate>20120701</enddate><creator>Kumar, Shashi Ranjan</creator><creator>Rao, Sachit</creator><creator>Ghose, Debasish</creator><general>American Institute of Aeronautics and Astronautics</general><scope>IQODW</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7SC</scope><scope>7SP</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>JQ2</scope><scope>L7M</scope><scope>L~C</scope><scope>L~D</scope></search><sort><creationdate>20120701</creationdate><title>Sliding-Mode Guidance and Control for All-Aspect Interceptors with Terminal Angle Constraints</title><author>Kumar, Shashi Ranjan ; Rao, Sachit ; Ghose, Debasish</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a478t-2b298fc4c28e6e12bd5a04fd37b6f409b5b34eb233b31cab08b457498090c2df3</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2012</creationdate><topic>Acceleration</topic><topic>Aerospace engineering</topic><topic>Aircraft</topic><topic>Angles (geometry)</topic><topic>Applied sciences</topic><topic>Automatic pilots</topic><topic>Autopilots</topic><topic>Computer science; control theory; systems</topic><topic>Control system synthesis</topic><topic>Control theory. Systems</topic><topic>Design</topic><topic>Exact sciences and technology</topic><topic>Impact angle</topic><topic>Interceptors</topic><topic>Laws</topic><topic>Missiles</topic><topic>Nonlinear dynamics</topic><topic>Terminals</topic><topic>Velocity</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Kumar, Shashi Ranjan</creatorcontrib><creatorcontrib>Rao, Sachit</creatorcontrib><creatorcontrib>Ghose, Debasish</creatorcontrib><collection>Pascal-Francis</collection><collection>CrossRef</collection><collection>Computer and Information Systems Abstracts</collection><collection>Electronics & Communications Abstracts</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>ProQuest Computer Science Collection</collection><collection>Advanced Technologies Database with Aerospace</collection><collection>Computer and Information Systems Abstracts Academic</collection><collection>Computer and Information Systems Abstracts Professional</collection><jtitle>Journal of guidance, control, and dynamics</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Kumar, Shashi Ranjan</au><au>Rao, Sachit</au><au>Ghose, Debasish</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Sliding-Mode Guidance and Control for All-Aspect Interceptors with Terminal Angle Constraints</atitle><jtitle>Journal of guidance, control, and dynamics</jtitle><date>2012-07-01</date><risdate>2012</risdate><volume>35</volume><issue>4</issue><spage>1230</spage><epage>1246</epage><pages>1230-1246</pages><issn>0731-5090</issn><eissn>1533-3884</eissn><coden>JGCODS</coden><abstract>In this paper, sliding-mode-control-based guidance laws to intercept stationary, constant-velocity, and maneuvering targets at a desired impact angle are proposed. The desired impact angle, which is defined in terms of a desired line-of-sight angle, is achieved in finite time by selecting the missile's lateral acceleration to enforce terminal sliding mode on a switching surface designed using nonlinear engagement dynamics. The conditions for capturability are also presented. In addition, by considering a three-degree-of-freedom linear-interceptor dynamic model and by following the procedure used to design a dynamic sliding-mode controller, the interceptor autopilot is designed as a simple static controller to track the lateral acceleration generated by the guidance law. Numerical simulation results are presented to validate the proposed guidance laws and the autopilot design for different initial engagement geometries and impact angles.</abstract><cop>Reston, VA</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/1.55242</doi><tpages>17</tpages></addata></record> |
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| identifier | ISSN: 0731-5090 |
| ispartof | Journal of guidance, control, and dynamics, 2012-07, Vol.35 (4), p.1230-1246 |
| issn | 0731-5090 1533-3884 |
| language | eng |
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| source | Alma/SFX Local Collection |
| subjects | Acceleration Aerospace engineering Aircraft Angles (geometry) Applied sciences Automatic pilots Autopilots Computer science control theory systems Control system synthesis Control theory. Systems Design Exact sciences and technology Impact angle Interceptors Laws Missiles Nonlinear dynamics Terminals Velocity |
| title | Sliding-Mode Guidance and Control for All-Aspect Interceptors with Terminal Angle Constraints |
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