FRANÇAIS
A showcase of ÉTS researchers’ publications and other contributions
SEARCH

Multidisciplinary optimization for weight saving in a variable tapered span-morphing wing using composite materials—application to the UAS-S4

Downloads

Downloads per month over past year

Elelwi, Mohamed, Pinto, Felipe Schiavoni, Botez, Ruxandra Mihaela et Dao, Thien My. 2022. « Multidisciplinary optimization for weight saving in a variable tapered span-morphing wing using composite materials—application to the UAS-S4 ». Actuators, vol. 11, nº 5.

[thumbnail of Botez-R-2022-24432.pdf]
Preview
PDF
Botez-R-2022-24432.pdf - Published Version
Use licence: Creative Commons CC BY.

Download (32MB) | Preview

Abstract

This paper is a follow-up to earlier work on applying multidisciplinary numerical optimiza- tion to develop a morphing variable span of a tapered wing (MVSTW) to reduce its weight by using composite materials. This study creates a numerical environment of multidisciplinary optimization by integrating material selection, structural sizing, and topological optimization following aerodynamic optimization results with the aim to assess whether morphing wing optimization is feasible. This sophisticated technology is suggested for developing MVSTWs. As a first step, a problem-specific optimization approach is described for specifying the weight-saving structure of wing components using composite materials. The optimization was performed using several approaches; for example, aerodynamic optimization was performed with CFD and XFLR5 codes, the material selection was conducted using MATLAB code, and sizing and topology optimization was carried out using Altair’s OptiStruct and SolidThinking Inspire solvers. The goal of this research is to achieve the MVSTW’s structural rigidity standards by minimizing wing components’ weight while maximizing stiffness. According to the results of this optimization, the weight of the MVSTW was reduced significantly to 5.5 kg in comparison to the original UAS-S4 wing weight of 6.5kg. The optimization and Finite Element Method results also indicate that the developedmorphing variable span of a tapered wing can complete specified flight missions perfectly and without any mechanical breakdown.

Item Type: Peer reviewed article published in a journal
Professor:
Professor
Botez, Ruxandra
Dao, Thien-My
Affiliation: Génie des systèmes, Génie mécanique
Date Deposited: 02 Jun 2022 19:07
Last Modified: 23 Jun 2022 15:31
URI: https://espace2.etsmtl.ca/id/eprint/24432

Actions (login required)

View Item View Item