Robust autopilot design for STT missiles with multiple disturbances using twisting control.
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| Title: | Robust autopilot design for STT missiles with multiple disturbances using twisting control. |
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| Authors: | Han, Tuo1 hantuowm@hotmail.com, Hu, Qinglei1 |
| Source: | Aerospace Science & Technology. Nov2017, Vol. 70, p428-434. 7p. |
| Subjects: | Robust control, Automatic pilot (Airplanes), Nonlinear systems, Sliding mode control, PID controllers |
| Abstract: | In this paper, a novel second-order sliding mode control (NSOSMC) scheme with finite time convergence is proposed for the autopilot design of skid-to-turn (STT) missiles considering coupling effects to track the desired maneuver commands. Firstly, the control system formulation is developed based on the mathematical model for nonlinear missile dynamics with system uncertainties and unknown multiple disturbances. Secondly, the NSOSMC scheme is developed by using a PID sliding mode surface with twisting control algorithm, which is to suppress the system uncertainties and unknown external disturbances, and to eliminate the chattering phenomenon. Then, the proposed NSOSMC law is proved to be finite time convergent to the origin. Finally, the effectiveness and robustness of the proposed NSOSMC scheme is verified through the numerical simulations with comparisons. [ABSTRACT FROM AUTHOR] |
| Copyright of Aerospace Science & Technology is the property of Elsevier B.V. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.) | |
| Database: | Engineering Source |
| FullText | Text: Availability: 0 |
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| Header | DbId: egs DbLabel: Engineering Source An: 125610870 AccessLevel: 6 PubType: Academic Journal PubTypeId: academicJournal PreciseRelevancyScore: 0 |
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| Items | – Name: Title Label: Title Group: Ti Data: Robust autopilot design for STT missiles with multiple disturbances using twisting control. – Name: Author Label: Authors Group: Au Data: <searchLink fieldCode="AR" term="%22Han%2C+Tuo%22">Han, Tuo</searchLink><relatesTo>1</relatesTo><i> hantuowm@hotmail.com</i><br /><searchLink fieldCode="AR" term="%22Hu%2C+Qinglei%22">Hu, Qinglei</searchLink><relatesTo>1</relatesTo> – Name: TitleSource Label: Source Group: Src Data: <searchLink fieldCode="JN" term="%22Aerospace+Science+%26+Technology%22">Aerospace Science & Technology</searchLink>. Nov2017, Vol. 70, p428-434. 7p. – Name: Subject Label: Subjects Group: Su Data: <searchLink fieldCode="DE" term="%22Robust+control%22">Robust control</searchLink><br /><searchLink fieldCode="DE" term="%22Automatic+pilot+%28Airplanes%29%22">Automatic pilot (Airplanes)</searchLink><br /><searchLink fieldCode="DE" term="%22Nonlinear+systems%22">Nonlinear systems</searchLink><br /><searchLink fieldCode="DE" term="%22Sliding+mode+control%22">Sliding mode control</searchLink><br /><searchLink fieldCode="DE" term="%22PID+controllers%22">PID controllers</searchLink> – Name: Abstract Label: Abstract Group: Ab Data: In this paper, a novel second-order sliding mode control (NSOSMC) scheme with finite time convergence is proposed for the autopilot design of skid-to-turn (STT) missiles considering coupling effects to track the desired maneuver commands. Firstly, the control system formulation is developed based on the mathematical model for nonlinear missile dynamics with system uncertainties and unknown multiple disturbances. Secondly, the NSOSMC scheme is developed by using a PID sliding mode surface with twisting control algorithm, which is to suppress the system uncertainties and unknown external disturbances, and to eliminate the chattering phenomenon. Then, the proposed NSOSMC law is proved to be finite time convergent to the origin. Finally, the effectiveness and robustness of the proposed NSOSMC scheme is verified through the numerical simulations with comparisons. [ABSTRACT FROM AUTHOR] – Name: AbstractSuppliedCopyright Label: Group: Ab Data: <i>Copyright of Aerospace Science & Technology is the property of Elsevier B.V. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.) |
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| RecordInfo | BibRecord: BibEntity: Identifiers: – Type: doi Value: 10.1016/j.ast.2017.08.026 Languages: – Code: eng Text: English PhysicalDescription: Pagination: PageCount: 7 StartPage: 428 Subjects: – SubjectFull: Robust control Type: general – SubjectFull: Automatic pilot (Airplanes) Type: general – SubjectFull: Nonlinear systems Type: general – SubjectFull: Sliding mode control Type: general – SubjectFull: PID controllers Type: general Titles: – TitleFull: Robust autopilot design for STT missiles with multiple disturbances using twisting control. Type: main BibRelationships: HasContributorRelationships: – PersonEntity: Name: NameFull: Han, Tuo – PersonEntity: Name: NameFull: Hu, Qinglei IsPartOfRelationships: – BibEntity: Dates: – D: 01 M: 11 Text: Nov2017 Type: published Y: 2017 Identifiers: – Type: issn-print Value: 12709638 Numbering: – Type: volume Value: 70 Titles: – TitleFull: Aerospace Science & Technology Type: main |
| ResultId | 1 |
