Gust Alleviation of Aeroelastic Aircraft Using CFD Simulation

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F18%3AN0000030" target="_blank" >RIV/00010669:_____/18:N0000030 - isvavai.cz</a>

Výsledek na webu

<a href="https://www.sciencedirect.com/science/article/pii/S2352146518300371" target="_blank" >https://www.sciencedirect.com/science/article/pii/S2352146518300371</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1016/j.trpro.2018.02.033" target="_blank" >10.1016/j.trpro.2018.02.033</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Gust Alleviation of Aeroelastic Aircraft Using CFD Simulation

Popis výsledku v původním jazyce

A CFD study of a gust alleviation technique based on the use of aircraft’s control surfaces on the main wing and on the horizontal tail plane is presented. The NASA Common Research model of an airliner is used as the reference configuration. The gust model is based on adding artificial gust velocities into the governing equations, so-called Disturbance Velocity Approach. The gust is identified as a change in the Angle of Attack upstream of the aircraft nose. A series of gusts is used to measure response of the aircraft and to establish the dynamic gust model. The elasticity of the aircraft model is taken into account employing modal analysis and the response of the aircraft structure is studied. The movable control surfaces are defined and characterized by CFD using the mesh deformation technique in the unsteady RANS simulations. Finally, the dynamic model based on both the gust data on one hand and on the control surfaces on the other is exploited to define the controller with the aim to alleviate the gust. The required time response of the movable control surfaces is studied to clarify limits of this alleviation technique.

Název v anglickém jazyce

Gust Alleviation of Aeroelastic Aircraft Using CFD Simulation

Popis výsledku anglicky

A CFD study of a gust alleviation technique based on the use of aircraft’s control surfaces on the main wing and on the horizontal tail plane is presented. The NASA Common Research model of an airliner is used as the reference configuration. The gust model is based on adding artificial gust velocities into the governing equations, so-called Disturbance Velocity Approach. The gust is identified as a change in the Angle of Attack upstream of the aircraft nose. A series of gusts is used to measure response of the aircraft and to establish the dynamic gust model. The elasticity of the aircraft model is taken into account employing modal analysis and the response of the aircraft structure is studied. The movable control surfaces are defined and characterized by CFD using the mesh deformation technique in the unsteady RANS simulations. Finally, the dynamic model based on both the gust data on one hand and on the control surfaces on the other is exploited to define the controller with the aim to alleviate the gust. The required time response of the movable control surfaces is studied to clarify limits of this alleviation technique.

Druh

D - Stať ve sborníku

CEP obor

—

OECD FORD obor

20304 - Aerospace engineering

Projekt

—

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2018

Kód důvěrnosti údajů

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

Název statě ve sborníku

Transportation Research Procedia

ISBN

—

ISSN

2352-1457

e-ISSN

2352-1465

Počet stran výsledku

10

Strana od-do

366-375

Název nakladatele

Elsevier Science B.V.

Místo vydání

Neuveden

Místo konání akce

Bukurešť, Rumunsko

Datum konání akce

16. 10. 2017

Typ akce podle státní příslušnosti

EUR - Evropská akce

Kód UT WoS článku

000454701600033