Unified model of sandwich panel core and faces for aeroelastic optimization

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F26%3A0193832" target="_blank" >RIV/00216305:26210/26:0193832 - isvavai.cz</a>

Výsledek na webu

<a href="https://conf.ifasd2024.nl/proceedings/display_manuscript/133.htm" target="_blank" >https://conf.ifasd2024.nl/proceedings/display_manuscript/133.htm</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Unified model of sandwich panel core and faces for aeroelastic optimization

Popis výsledku v původním jazyce

Metamaterials show a considerable potential in the field of complex optimization of aerospace structures. To fully exploit this potential, the authors present a novel approach to modeling the structural response of a sandwich panel with metamaterial core and CFRP skins that could be used within a single-step optimization process. The proposed approach is illustrated using a model of a panel with aluminum honeycomb core. Obtained results confirm the high potential of the inclusion of the core optimization into the optimization framework. Simple preliminary validation utilizing the finite element analysis presented in the closure of this study yielded a satisfactory agreement with the results of the proposed analytical model. The maximum reached difference of five percent can be attributed to a different shape of deformation of the honeycomb core within the sandwich as opposed to a deformation of the honeycomb core alone.

Název v anglickém jazyce

Unified model of sandwich panel core and faces for aeroelastic optimization

Popis výsledku anglicky

Metamaterials show a considerable potential in the field of complex optimization of aerospace structures. To fully exploit this potential, the authors present a novel approach to modeling the structural response of a sandwich panel with metamaterial core and CFRP skins that could be used within a single-step optimization process. The proposed approach is illustrated using a model of a panel with aluminum honeycomb core. Obtained results confirm the high potential of the inclusion of the core optimization into the optimization framework. Simple preliminary validation utilizing the finite element analysis presented in the closure of this study yielded a satisfactory agreement with the results of the proposed analytical model. The maximum reached difference of five percent can be attributed to a different shape of deformation of the honeycomb core within the sandwich as opposed to a deformation of the honeycomb core alone.

Druh

D - Stať ve sborníku

CEP obor

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OECD FORD obor

20304 - Aerospace engineering

Projekt

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Návaznosti

S - Specificky vyzkum na vysokych skolach

Rok uplatnění

2024

Kód důvěrnosti údajů

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

Název statě ve sborníku

International Forum on Aeroelasticity and Structural Dynamics, IFASD 2024

ISBN

9788409423538

ISSN

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e-ISSN

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Počet stran výsledku

13

Strana od-do

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Název nakladatele

International Forum on Aeroelasticity and Structural Dynamics (IFASD)

Místo vydání

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Místo konání akce

Hague, Netherlands   

Datum konání akce

17. 6. 2024

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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