Nonlinear control for missile terminal guidance
| dc.citation.epage | 668 | en_US |
| dc.citation.issue | 4 | en_US |
| dc.citation.spage | 663 | en_US |
| dc.citation.volume | 122 | en_US |
| dc.citation.woscount | 21 | |
| dc.contributor.author | Liaw, DC | en_US |
| dc.contributor.author | Liang, YW | en_US |
| dc.contributor.author | Cheng, CC | en_US |
| dc.contributor.department | 電控工程研究所 | zh_TW |
| dc.contributor.department | Institute of Electrical and Control Engineering | en_US |
| dc.date.accessioned | 2014-12-08T15:44:36Z | |
| dc.date.available | 2014-12-08T15:44:36Z | |
| dc.date.issued | 2000-12-01 | en_US |
| dc.description.abstract | Variable Structure Control (VSC) technique is applied to the design of robust homing missile guidance laws. In the design procedure, the target's maneuver is assumed to be unpredictable and is considered as disturbances. Guidance laws are then proposed to achieve the interception performance for both cases of longitude-axis control being available and unavailable. The proposed guidance laws are continuous which alleviate chattering drawback by classic VSC design. Results are obtained and compared with those by realistic true proportional navigation design to illustrate the benefits of the proposed decision. [S0022-0434(00)00604-3]. | en_US |
| dc.identifier.issn | 0022-0434 | en_US |
| dc.identifier.journal | JOURNAL OF DYNAMIC SYSTEMS MEASUREMENT AND CONTROL-TRANSACTIONS OF THE ASME | en_US |
| dc.identifier.uri | https://ir.lib.nycu.edu.tw/handle/11536/30119 | |
| dc.identifier.wosnumber | WOS:000167109200013 | |
| dc.language.iso | en_US | en_US |
| dc.title | Nonlinear control for missile terminal guidance | en_US |
| dc.type | Article | en_US |