Preliminary design of morphing flaperon using optimization by genetic algorithm

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F26%3A0198270" target="_blank" >RIV/00216305:26210/26:0198270 - isvavai.cz</a>

Výsledek na webu

<a href="https://www.emerald.com/insight/content/doi/10.1108/aeat-11-2024-0329/full/html" target="_blank" >https://www.emerald.com/insight/content/doi/10.1108/aeat-11-2024-0329/full/html</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1108/AEAT-11-2024-0329" target="_blank" >10.1108/AEAT-11-2024-0329</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Preliminary design of morphing flaperon using optimization by genetic algorithm

Popis výsledku v původním jazyce

Purpose This article presents an approach to morphing flaperon design. The presented design workflow attempts a simple structural arrangement of trailing edge morphing for applicability in the short term. The purpose of this paper is to test the optimization of the geometry built in for future multidisciplinary flaperon optimization techniques.Design/methodology/approach To meet the contrary requirements on stiffness and compliance of the morphing structure, the design is performed as a multi-objective optimization problem solved using a genetic algorithm. The objective function for optimization incorporates the failure index, target deflection and actuation force for both upper and lower deflection. To produce the single objective value a weighting is used. The constraints and conditions are used to reduce the resulting dependency on weighting factors selection. The described problem was solved using Matlab scripting, combined with a structural Nastran finite element method solver to determine individual's properties for evaluation and selection.Findings The problem formulation and design workflow fulfill the goal. The obtained set of parameters defines the morphing flaperon geometry, that allows achieving the described deflections with the required failure indexes and with minimal actuation force, therefore verifying the morphing mechanism. The design workflow proved feasible and will be further developed.Originality/value The presented workflow allows to find the geometry for specified material properties and airfoil shape. Therefore, an engineering approach is offered to assess the combination structurally for the specified deflection range with minimal actuation force. The morphing trailing edge in combination with a laminar airfoil has not been given much attention yet.

Název v anglickém jazyce

Preliminary design of morphing flaperon using optimization by genetic algorithm

Popis výsledku anglicky

Purpose This article presents an approach to morphing flaperon design. The presented design workflow attempts a simple structural arrangement of trailing edge morphing for applicability in the short term. The purpose of this paper is to test the optimization of the geometry built in for future multidisciplinary flaperon optimization techniques.Design/methodology/approach To meet the contrary requirements on stiffness and compliance of the morphing structure, the design is performed as a multi-objective optimization problem solved using a genetic algorithm. The objective function for optimization incorporates the failure index, target deflection and actuation force for both upper and lower deflection. To produce the single objective value a weighting is used. The constraints and conditions are used to reduce the resulting dependency on weighting factors selection. The described problem was solved using Matlab scripting, combined with a structural Nastran finite element method solver to determine individual's properties for evaluation and selection.Findings The problem formulation and design workflow fulfill the goal. The obtained set of parameters defines the morphing flaperon geometry, that allows achieving the described deflections with the required failure indexes and with minimal actuation force, therefore verifying the morphing mechanism. The design workflow proved feasible and will be further developed.Originality/value The presented workflow allows to find the geometry for specified material properties and airfoil shape. Therefore, an engineering approach is offered to assess the combination structurally for the specified deflection range with minimal actuation force. The morphing trailing edge in combination with a laminar airfoil has not been given much attention yet.

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

—

OECD FORD obor

20304 - Aerospace engineering

Projekt

—

Návaznosti

S - Specificky vyzkum na vysokych skolach

Rok uplatnění

2025

Kód důvěrnosti údajů

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

Název periodika

Aircraft Engineering and Aerospace Technology: An International Journal

ISSN

0002-2667

e-ISSN

—

Svazek periodika

97

Číslo periodika v rámci svazku

7

Stát vydavatele periodika

GB - Spojené království Velké Británie a Severního Irska

Počet stran výsledku

10

Strana od-do

754-763

Kód UT WoS článku

001513505300001

EID výsledku v databázi Scopus

2-s2.0-105008283312