Please use this identifier to cite or link to this item:
http://hdl.handle.net/10397/92789
DC Field | Value | Language |
---|---|---|
dc.contributor | Department of Aeronautical and Aviation Engineering | - |
dc.creator | Wang, X | en_US |
dc.creator | Van, Kampen, EJ | en_US |
dc.creator | Chu, Q | en_US |
dc.creator | Lu, P | en_US |
dc.date.accessioned | 2022-05-16T09:07:46Z | - |
dc.date.available | 2022-05-16T09:07:46Z | - |
dc.identifier.issn | 0731-5090 | en_US |
dc.identifier.uri | http://hdl.handle.net/10397/92789 | - |
dc.language.iso | en | en_US |
dc.publisher | American Institute of Aeronautics and Astronautics, Inc. | en_US |
dc.rights | © 2018 by Xuerui Wang, Delft University of Technology | en_US |
dc.rights | This is the peer reviewed version of the following article: Wang, X., Kampen, E. J. V., Chu, Q., & Lu, P. (2019). Incremental sliding-mode fault-tolerant flight control. Journal of guidance, control, and dynamics, 42(2), 244-259 , which has been published in final form at https://doi.org/10.2514/1.G003497 | en_US |
dc.title | Incremental sliding-mode fault-tolerant flight control | en_US |
dc.type | Journal/Magazine Article | en_US |
dc.identifier.spage | 244 | en_US |
dc.identifier.epage | 259 | en_US |
dc.identifier.volume | 42 | en_US |
dc.identifier.issue | 2 | en_US |
dc.identifier.doi | 10.2514/1.G003497 | en_US |
dcterms.abstract | This paper proposes a novel control framework that combines the recently reformulated incremental nonlinear dynamic inversion with (higher-order) sliding-mode controllers/observers, for generic multi-input/multi-output nonlinear systems, named incremental sliding-mode control. As compared to the widely used approach that designs (higher-order) sliding-mode controllers/observers based on nonlinear dynamic inversion, the proposed incremental framework can further reduce the uncertainties while requiring less model knowledge. Because the uncertainties are reduced in the incremental framework, theoretical analyses demonstrate that the incremental sliding-mode control can passively resist a wider range of perturbations with reduced minimum possible control/observer gains. These merits are validated via numerical simulations for aircraft command tracking problems, in the presence of sudden actuator faults and structural damage. | - |
dcterms.accessRights | open access | en_US |
dcterms.bibliographicCitation | Journal of guidance, control, and dynamics, Feb. 2019, v. 42, no. 2, p. 244-259 | en_US |
dcterms.isPartOf | Journal of guidance, control, and dynamics | en_US |
dcterms.issued | 2019-02 | - |
dc.identifier.scopus | 2-s2.0-85062891838 | - |
dc.identifier.eissn | 1533-3884 | en_US |
dc.description.validate | 202205 bckw | - |
dc.description.oa | Accepted Manuscript | en_US |
dc.identifier.FolderNumber | AAE-0117 | - |
dc.description.fundingSource | Self-funded | en_US |
dc.description.pubStatus | Published | en_US |
dc.identifier.OPUS | 26474598 | - |
Appears in Collections: | Journal/Magazine Article |
Files in This Item:
File | Description | Size | Format | |
---|---|---|---|---|
Lu_Incremental_Sliding-Mode_Fault-Tolerant.pdf | Pre-Published version | 3.12 MB | Adobe PDF | View/Open |
Page views
58
Last Week
0
0
Last month
Citations as of Apr 21, 2024
Downloads
34
Citations as of Apr 21, 2024
SCOPUSTM
Citations
75
Citations as of Apr 26, 2024
WEB OF SCIENCETM
Citations
57
Citations as of Apr 25, 2024
Google ScholarTM
Check
Altmetric
Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.