Topometry FEM optimization of the wing structure of the transport aircraft

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F17%3APU123214" target="_blank" >RIV/00216305:26210/17:PU123214 - isvavai.cz</a>

Výsledek na webu

<a href="http://www.tandfonline.com/doi/abs/10.3846/16487788.2016.1266819" target="_blank" >http://www.tandfonline.com/doi/abs/10.3846/16487788.2016.1266819</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.3846/16487788.2016.1266819" target="_blank" >10.3846/16487788.2016.1266819</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Topometry FEM optimization of the wing structure of the transport aircraft

Popis výsledku v původním jazyce

The article presents the topometry optimization of the critical semi-shell wing structure of the aircraft in the Commuter category of the CS-23 regulation standard (EASA 2012). Modern finite element (FE) optimization methods are used. The main outcome is that the milled integral lower wing panel allows significant weight savings due to an optimization of the thickness of each skin segment. The FE model validation with the analytical software and the selection of structural constraints and requirements for the optimization are described in this article. Also, a final stress analysis and a complex load capacity analysis validate required properties of designed structural modifications with an optimal stress distribution. Additionally the analysis of weight savings and elongation of the fatigue durability according to the Damage tolerance methodology was done.

Název v anglickém jazyce

Topometry FEM optimization of the wing structure of the transport aircraft

Popis výsledku anglicky

The article presents the topometry optimization of the critical semi-shell wing structure of the aircraft in the Commuter category of the CS-23 regulation standard (EASA 2012). Modern finite element (FE) optimization methods are used. The main outcome is that the milled integral lower wing panel allows significant weight savings due to an optimization of the thickness of each skin segment. The FE model validation with the analytical software and the selection of structural constraints and requirements for the optimization are described in this article. Also, a final stress analysis and a complex load capacity analysis validate required properties of designed structural modifications with an optimal stress distribution. Additionally the analysis of weight savings and elongation of the fatigue durability according to the Damage tolerance methodology was done.

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

—

OECD FORD obor

20304 - Aerospace engineering

Projekt

<a href="/cs/project/TE02000032" target="_blank" >TE02000032: Výzkumné centrum pokročilých leteckých konstrukcí</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2017

Kód důvěrnosti údajů

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

Název periodika

AVIATION

ISSN

1648-7788

e-ISSN

—

Svazek periodika

2017

Číslo periodika v rámci svazku

21

Stát vydavatele periodika

LT - Litevská republika

Počet stran výsledku

6

Strana od-do

29-34

Kód UT WoS článku

000398819400005

EID výsledku v databázi Scopus

2-s2.0-85016433245