Please use this identifier to cite or link to this item: https://scholarbank.nus.edu.sg/handle/10635/115476
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dc.titleReliable automatic landing control against actuator stuck faults
dc.contributor.authorLiao, F.
dc.contributor.authorWang, J.L.
dc.contributor.authorPoh, E.K.
dc.contributor.authorLi, D.
dc.date.accessioned2014-12-12T07:16:04Z
dc.date.available2014-12-12T07:16:04Z
dc.date.issued2004
dc.identifier.citationLiao, F.,Wang, J.L.,Poh, E.K.,Li, D. (2004). Reliable automatic landing control against actuator stuck faults. Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 4 : 2283-2295. ScholarBank@NUS Repository.
dc.identifier.isbn1563476703
dc.identifier.urihttp://scholarbank.nus.edu.sg/handle/10635/115476
dc.description.abstractThis paper presents a new LMI-based approach for developing reliable automatic landing controllers which can tolerate actuator stuck faults. The H 2 control technique is used to guarantee tracking performance with respect to a given glide slope trajectory. A realistic fighter aircraft model is studied to illustrate the proposed approach. Nonlinear simulation under various faults and wind disturbances are included in this study. Simulation results show that the proposed reliable controller design approach can achieve zero steady-state tracking error, robustness against wind disturbances and reliability against actuator stuck faults. Copyright © 2004 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
dc.sourceScopus
dc.subjectActuator stuck faults
dc.subjectAffine parameter-dependent lyapunov functions
dc.subjectAutomatic landing
dc.subjectH 2 norm
dc.subjectReliable control
dc.typeConference Paper
dc.contributor.departmentTEMASEK LABORATORIES
dc.description.sourcetitleCollection of Technical Papers - AIAA Guidance, Navigation, and Control Conference
dc.description.volume4
dc.description.page2283-2295
dc.identifier.isiutNOT_IN_WOS
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