Interaction of self-excited and delayed forced excitation on blade bunch

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F16%3A00462734" target="_blank" >RIV/61388998:_____/16:00462734 - isvavai.cz</a>

Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Interaction of self-excited and delayed forced excitation on blade bunch

Popis výsledku v původním jazyce

This paper deals with control of chaos in a non-linear aeroelastic pitch-plunge model for aircraft wings. While design of non-linear controllers to asymptotically stabilize the initial bifurcation exists in the current literature, the primary goal of this paper is to control the chaotic motion using feedback linearization. For this purpose, a pitch-plunge model with two flaps is considered for the study. The approach proposed for the control of chaos is that of a tracking problem where the system is controlled to a defined limit cycle; thus the chaotic motion is replaced by orbital stability. Using Lie Algebra, a feedback linearization is performed by transforming from the non-linear space to a linear one. The error dynamics is established as the deviation of the chaotic trajectory from that of the desired path and tracking is attained by reducing the error to zero. The ability of this approach to control chaos is demonstrated for a certain set of parameters of the pitch-plunge model, chosen from the literature.

Název v anglickém jazyce

Interaction of self-excited and delayed forced excitation on blade bunch

Popis výsledku anglicky

This paper deals with control of chaos in a non-linear aeroelastic pitch-plunge model for aircraft wings. While design of non-linear controllers to asymptotically stabilize the initial bifurcation exists in the current literature, the primary goal of this paper is to control the chaotic motion using feedback linearization. For this purpose, a pitch-plunge model with two flaps is considered for the study. The approach proposed for the control of chaos is that of a tracking problem where the system is controlled to a defined limit cycle; thus the chaotic motion is replaced by orbital stability. Using Lie Algebra, a feedback linearization is performed by transforming from the non-linear space to a linear one. The error dynamics is established as the deviation of the chaotic trajectory from that of the desired path and tracking is attained by reducing the error to zero. The ability of this approach to control chaos is demonstrated for a certain set of parameters of the pitch-plunge model, chosen from the literature.

Druh

D - Stať ve sborníku

CEP obor

BI - Akustika a kmity

OECD FORD obor

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Projekt

<a href="/cs/project/GA16-04546S" target="_blank" >GA16-04546S: Aeroelastické vazby a dynamické chování rotačně periodických těles</a><br>

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2016

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název statě ve sborníku

VETOMAC-XII

ISBN

978-83-61021-69-8

ISSN

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e-ISSN

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Počet stran výsledku

10

Strana od-do

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Název nakladatele

Wydawnictwo Instytutu Technicznego Wojsk Lotniczych

Místo vydání

Warszawa

Místo konání akce

Warsaw

Datum konání akce

7. 9. 2016

Typ akce podle státní příslušnosti

EUR - Evropská akce

Kód UT WoS článku

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