New control methodology for a morphing wing demonstrator

Kammegne, Michel Joël Tchatchueng; Tondji, Yvan; Botez, Ruxandra Mihaela; Grigorie, Teodor Lucian; Mamou, Mahmoud; Mébarki, Youssef

doi:10.1177/0954410017699003

Cited by 11 publications

(1 citation statement)

References 27 publications

(34 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The primary objective of this investigation is the distribution of the wing components inside the MVSTW design, while supporting its baseline structural integrity. The CFD code collected the applied pressure values for extreme flight conditions to achieve this objective (30) . The initial wing components were located by using the TO by matching the aerodynamic loads on the fixed and moving wing segments to achieve a required level of structural mechanical behaviour, such as deformation, stress and strain, for a robust structure (31) .…”

Section: Topology Optimisation Methodsmentioning

confidence: 99%

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

et al. 2021

View full text Add to dashboard Cite

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.

show abstract

Section: Topology Optimisation Methodsmentioning

confidence: 99%

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

et al. 2021

View full text Add to dashboard Cite

show abstract

Design and experimental testing of a control system for a morphing wing model actuated with miniature BLDC motors

Grigorie

Khan²,

Botez³

et al. 2020

Chinese Journal of Aeronautics

View full text Add to dashboard Cite

Development of an SMA-based camber morphing UAV tail core design

Bishay

Finden

Recinos

et al. 2019

Smart Mater. Struct.

View full text Add to dashboard Cite

This paper presents a new design for the core of a lightweight tail section of an unmanned aerial vehicle (UAV) with camber-morphing horizontal and vertical stabilizers. The core of each stabilizer is composed of an aluminum spar, two active end ribs, and multiple inactive ribs. Each active end rib is composed of a solid leading compartment connected to a flexible corrugated trailing segment. Thermally activated shape memory alloy (SMA) wire actuators along the length of the corrugated segment are used to control the camber of each active rib. The SMA wires are extended through the hollow spar to increase the amount of actuation and are guided using polycarbonate pulleys. A parametric CAD model was created to automatically regenerate the corrugated trailing segment geometry based on trough height, width and angle, as well as the used NACA airfoil. The locations of the vertical webs are adjusted with each parameter set so that the webs are always at the trough centers for consistency. COMSOL's LiveLink was used to pass the generated CAD geometry to COMSOL, where finite element structural analysis is performed to study the effect of the geometric parameters on the camber deformation under SMA wire actuation and applied loads. The deformed shape of the trailing segment is then approximated as a third-degree polynomial and used to modify the four-digit NACA airfoil equation, generating a deformed shape for the airfoil. 2D computational fluid dynamics simulations are then performed to compute the lift-to-drag ratio for each structural configuration, from which the geometric parameters that maximize the performance of the stabilizer at the design speed can be selected. The proposed UAV SMA-based camber-morphing rear control section has been successfully manufactured and tested. Camber morphing up to 10.7°was successfully achieved and showed very good agreement with the numerical prediction.

show abstract

New control methodology for a morphing wing demonstrator

Cited by 11 publications

References 27 publications

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

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

Design and experimental testing of a control system for a morphing wing model actuated with miniature BLDC motors

Development of an SMA-based camber morphing UAV tail core design

Contact Info

Product

Resources

About