Methodology for the design and optimization of a morphing wing droop-nose structure for greener aircraft

Pecorella, Daniele (2022) Methodology for the design and optimization of a morphing wing droop-nose structure for greener aircraft. [Laurea magistrale], Università di Bologna, Corso di Studio in Aerospace engineering / ingegneria aerospaziale [LM-DM270] - Forli', Documento full-text non disponibile
Il full-text non è disponibile per scelta dell'autore. (Contatta l'autore)


Droop-Nose Leading Edge (DNLE) morphing wings are one of the most promising devices in order to achieve aerodynamic drag and noise reduction during take-off and landing phases. An accurate design of these structures could lead to the decrease of aircraft fuel consumption in the perspective of reaching a greener aviation, following the objectives indicated by Flightpath 2050 issued by the E.U. However, due to the challenges related to the realization of this technology and TRL reached, DNLE are more likely implemented in Unmanned Aerial Systems (UAS) for testing and evaluation purposes. In the present study, an optimization methodology for the DNLE composite laminate skin and morphing mechanism structure is proposed and applied to a study case represented by the UAS-S45 aircraft. The work starts from the morphing leading edge structure developed by the LARCASE laboratory at ETS Montreal. The results showed that by means of the optimization strategy adopted, the force required on the actuator mechanism is 88% lower than the original design. A significant improvement on the profile smoothness along its section and in the spanwise direction in morphing conditions has been obtained too. However, further investigations are still needed in order to achieve a more appropriate morphing shape. Despite this, it appears from the results obtained that the proposed methodology can be useful to tackle the DNLE design problem in an effective and efficient way. What developed in this work has been conceived to support the investigation of DNLE in the small leading edge profiles typical of the UAS. In this way, an easier procedure for the set up of the design flow, and a decrease in the computational effort for the optimization process can be obtained. An experimental validation of the results obtained is currently being performed at ETS, and future development regards the assessment of the errors of the numeric procedure herein presented respect to real data.

Tipologia del documento
Tesi di laurea (Laurea magistrale)
Autore della tesi
Pecorella, Daniele
Relatore della tesi
Correlatore della tesi
Corso di studio
Ordinamento Cds
Parole chiave
Optimization,Wing morphing,FEM,aviation,droop nose leading edge,structural analysis,genetic algorithm,particle swarm optimization,wing,composite laminate,composite material,aircraft,PATRAN,NASTRAN,parametrization,experimental validation,climate change,flightpath 2050,green aviation,variable camber wing,morphing leading edge,airfoil,morphing skin,morphing mechanism,non linear FEM analysis,cost function,UAV,Unmanned Aerial Systems,3d modelling,CAD,Finite element analysis,python,MATLAB,Solidworks
Data di discussione della Tesi
24 Marzo 2022

Altri metadati

Gestione del documento: Visualizza il documento