The design of new eVTOL (electric vertical take-off and landing) multi-propeller aircraft configurations for advanced air mobility requires new tools and studies, both experimental and analytical. This thesis, in the context of a project initiated by Leonardo SpA Helicopter Division (LHD), presents a cost-effective design of a double-propeller (Lift/Thrust Unit (LTU)) test rig capable of measuring all the six components of its static and high-frequency dynamic loads while simultaneously and effectively controlling its RPM (revolutions per minute) in a closed-loop manner. In the first chapter, the design of the structure of the aforementioned test bench is presented. The mechanical design was driven by numerous requirements but above all by the need to test the two LTUs in relative positions and arbitrary angles of attack and by the objective of having a structure as stiff as possible. In chapter 2 the design of the closed loop RPM control is presented. This was necessary to ensure that designated test points (i.e. RPM conditions) were maintained during wind tunnel testing. Finally, in the final chapter, the data obtained during the wind tunnel tests are presented and analyzed in terms of both static and dynamic loads. This post-processed data will then be used for comparison and correlation with Leonardo's comprehensive simulation tools.
La progettazione di nuove configurazioni di velivoli multielica eVTOL (elettrico a decollo e atterraggio verticale) per la mobilità aerea avanzata richiede nuovi strumenti e studi, sia sperimentali che analitici. Questa tesi, nel contesto di un progetto avviato da Leonardo SpA Divisione Elicotteri (LHD), presenta la progettazione economicamente efficiente di un banco di prova a doppio rotore rigido azionato da motori elettrici, in grado di misurare tutte le sei componenti dei suoi carichi statici e dinamici ad alta frequenza, controllando simultaneamente ed efficacemente in anello chiuso la velocità dei due rotori. Nel primo capitolo viene presentato il progetto della struttura del suddetto banco prova. La progettazione meccanica è stata guidata da numerosi requisiti ma soprattutto dalla necessità di testare le due eliche in posizioni relative e angoli di attacco arbitrari, e dall'obiettivo di avere una struttura quanto più rigida possibile. Nel capitolo 2 viene presentata l'implementazione del controllo degli RPM in anello chiuso. Ciò era necessario per garantire che i punti di prova designati (ovvero le condizioni RPM) fossero mantenuti durante i test nella galleria del vento. Infine, nel capitolo finale, i dati ottenuti durante le prove in galleria del vento vengono presentati e analizzati sia in termini di carichi statici che dinamici. Questi dati post-elaborati verranno quindi utilizzati per il confronto e la correlazione con strumenti di simulazione di modelli aeroelastici di Leonardo.
Design and wind tunnel testing of a double electrical propeller system in the context of eVTOL aircrafts
Dispenza, Alberto
2023/2024
Abstract
The design of new eVTOL (electric vertical take-off and landing) multi-propeller aircraft configurations for advanced air mobility requires new tools and studies, both experimental and analytical. This thesis, in the context of a project initiated by Leonardo SpA Helicopter Division (LHD), presents a cost-effective design of a double-propeller (Lift/Thrust Unit (LTU)) test rig capable of measuring all the six components of its static and high-frequency dynamic loads while simultaneously and effectively controlling its RPM (revolutions per minute) in a closed-loop manner. In the first chapter, the design of the structure of the aforementioned test bench is presented. The mechanical design was driven by numerous requirements but above all by the need to test the two LTUs in relative positions and arbitrary angles of attack and by the objective of having a structure as stiff as possible. In chapter 2 the design of the closed loop RPM control is presented. This was necessary to ensure that designated test points (i.e. RPM conditions) were maintained during wind tunnel testing. Finally, in the final chapter, the data obtained during the wind tunnel tests are presented and analyzed in terms of both static and dynamic loads. This post-processed data will then be used for comparison and correlation with Leonardo's comprehensive simulation tools.File | Dimensione | Formato | |
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Design_and_Wind_Tunnel_Testing_of_a_Double_Electrical_Propeller_System_in_the_Context_of_eVTOL_Aircrafts___Dispenza.pdf
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Executive_Summary_Thesis___Design_and_Wind_Tunnel_Testing_of_a_Double_Electrical_Propeller_System_in_the_Context_of_eVTOL_Aircrafts___Dispenza.pdf
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https://hdl.handle.net/10589/218601