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Wing component allocation for a morphing variable span of tapered wing using finite element method and topology optimisation – application to the UAS-S4

Published online by Cambridge University Press:  07 June 2021

M. Elelwi ,
T. Calvet ,
R.M. Botez Open the ORCID record for R.M. Botez [Opens in a new window]  and
T.-M. Dao
M. Elelwi
Affiliation:
Laboratory of Active Controls, Avionics and AeroServoElasticity LARCASE, ÉTS - École de technologie supérieure, Montréal, QCH3C 1K3, Canada
T. Calvet
Affiliation:
Laboratory of Active Controls, Avionics and AeroServoElasticity LARCASE, ÉTS - École de technologie supérieure, Montréal, QCH3C 1K3, Canada
R.M. Botez*
Affiliation:
Laboratory of Active Controls, Avionics and AeroServoElasticity LARCASE, ÉTS - École de technologie supérieure, Montréal, QCH3C 1K3, Canada
T.-M. Dao
Affiliation:
Research Team in Machines Dynamics, Structures and Processes, ÉTS - École de technologie supérieure, Montréal, QCH3C 1K3, Canada
*
[email protected]
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Abstract

This work presents the Topology Optimisation of the Morphing Variable Span of Tapered Wing (MVSTW) using a finite element method. This topology optimisation aims to assess the feasibility of internal wing components such as ribs, spars and other structural components. This innovative approach is proposed for the telescopic mechanism of the MVSTW, which includes the sliding of the telescopically extended wing into the fixed wing segment. The optimisation is performed using the tools within ANSYS Mechanical, which allows the solving of topology optimisation problems. This study aims to minimise overall structural compliance and maximise stiffness to enhance structural performance, and thus to meet the structural integrity requirements of the MVSTW. The study evaluates the maximum displacements, stress and strain parameters of the optimised variable span morphing wing in comparison with those of the original wing. The optimised wing analyses are conducted on four wingspan extensions, that is, 0%, 25%, 50% and 75%, of the original wingspan, and for different flight speeds to include all flight phases (17, 34, 51 and 68m/s, respectively). Topology optimisation is carried out on the solid wing built with aluminium alloy 2024-T3 to distribute the wing components within the fixed and moving segments. The results show that the fixed and moving wing segments must be designed with two spar configurations, and seven ribs with their support elements in the high-strain area. The fixed and moving wing segments’ structural weight values were reduced to 16.3 and 10.3kg from 112 to 45kg, respectively. The optimised MVSTW was tested using different mechanical parameters such as strains, displacements and von Misses stresses. The results obtained from the optimised variable span morphing wing show the optimal mechanical behaviour and the structural wing integrity needed to achieve the multi-flight missions.

Keywords

Topology optimisationAerodynamic performanceTelescopic mechanismVariable span morphing of the tapered wingFinite element analysis
Type
Research Article
Information
The Aeronautical Journal , Volume 125 , Issue 1290 , August 2021 , pp. 1313 - 1336
Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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