DC Field | Value | Language |
---|---|---|
dc.contributor.author | Han, Tuo | ko |
dc.contributor.author | Shin, Hyo-Sang | ko |
dc.contributor.author | Hu, Qinglei | ko |
dc.contributor.author | Tsourdos, Antonios | ko |
dc.contributor.author | Xin, Ming | ko |
dc.date.accessioned | 2024-03-18T10:00:29Z | - |
dc.date.available | 2024-03-18T10:00:29Z | - |
dc.date.created | 2024-03-18 | - |
dc.date.issued | 2022-10 | - |
dc.identifier.citation | IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS, v.58, no.5, pp.4020 - 4032 | - |
dc.identifier.issn | 0018-9251 | - |
dc.identifier.uri | http://hdl.handle.net/10203/318568 | - |
dc.description.abstract | In this article, an incremental guidancelaw with terminal angle constraint is proposed against maneuvering targets in the 3-D space. First, a sliding surface is constructed such that its first-order dynamics excludes the relative range and line-of-sight angles in the perturbation. This manipulation avoids unboundedperturbations induced by target maneuvers near collision. Then, a benchmark guidance law is derived via the nonlinear dynamic inversion (NDI) based sliding mode control (NDI-SMC). To further enhance guidance system robustness, an incremental nonlinear dynamic inversion (INDI) based SMC (INDI-SMC) 3-D guidance law is developed. The INDI-SMC guidance law exploits the first-order derivative of the sliding variable and guidance command output at the latest step, which leads to reduced perturbation and thus requires smaller gains than the NDI-SMC guidance law. A multivariable continuous differentiator is employed to estimate the sliding variable's first-order derivative for guidance law implementation. Moreover, the stability of the differentiator is analyzed and the guidance robustness under uncertainties is compared. Extensive numerical simulations and a Monte Carlo test are conducted to verify effectiveness and robustness of the proposed method. | - |
dc.language | English | - |
dc.publisher | IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC | - |
dc.title | Differentiator-Based Incremental Three-Dimensional Terminal Angle Guidance With Enhanced Robustness | - |
dc.type | Article | - |
dc.identifier.wosid | 000866503000024 | - |
dc.identifier.scopusid | 2-s2.0-85126284572 | - |
dc.type.rims | ART | - |
dc.citation.volume | 58 | - |
dc.citation.issue | 5 | - |
dc.citation.beginningpage | 4020 | - |
dc.citation.endingpage | 4032 | - |
dc.citation.publicationname | IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS | - |
dc.identifier.doi | 10.1109/TAES.2022.3158639 | - |
dc.contributor.localauthor | Shin, Hyo-Sang | - |
dc.contributor.nonIdAuthor | Han, Tuo | - |
dc.contributor.nonIdAuthor | Hu, Qinglei | - |
dc.contributor.nonIdAuthor | Tsourdos, Antonios | - |
dc.contributor.nonIdAuthor | Xin, Ming | - |
dc.description.isOpenAccess | N | - |
dc.type.journalArticle | Article | - |
dc.subject.keywordAuthor | Three-dimensional displays | - |
dc.subject.keywordAuthor | Perturbation methods | - |
dc.subject.keywordAuthor | Robustness | - |
dc.subject.keywordAuthor | Missiles | - |
dc.subject.keywordAuthor | Nonlinear dynamical systems | - |
dc.subject.keywordAuthor | Sliding mode control | - |
dc.subject.keywordAuthor | Numerical simulation | - |
dc.subject.keywordAuthor | Differentiator | - |
dc.subject.keywordAuthor | incremental nonlinear dynamic inversion (INDI) | - |
dc.subject.keywordAuthor | sliding mode control (SMC) | - |
dc.subject.keywordAuthor | terminal angle constraint | - |
dc.subject.keywordAuthor | three-dimensional (3-D) guidance | - |
dc.subject.keywordPlus | SLIDING-MODE GUIDANCE | - |
dc.subject.keywordPlus | IMPACT-ANGLE | - |
dc.subject.keywordPlus | MANEUVERING TARGET | - |
dc.subject.keywordPlus | LAW | - |
dc.subject.keywordPlus | CONSTRAINT | - |
dc.subject.keywordPlus | DESIGN | - |
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