|Tipo di tesi||Tesi di laurea magistrale|
|Indirizzo firstname.lastname@example.org, email@example.com|
|Titolo||Progetto aerodinamico di un drone a decollo verticale ad ala fissa|
|Titolo in inglese||Aerodynamic design of a VTOL fixed wing UAV research platform|
|Struttura||Dipartimento di Ingegneria "Enzo Ferrari"|
|Corso di studi||Ingegneria Del Veicolo (D.M.270/04)|
|Data inizio appello||2014-12-10|
|Disponibilità||Accessibile via web (tutti i file della tesi sono accessibili)|
L’obiettivo di questa tesi è il progetto aerodinamico di un drone volante ad ala fissa capace di decollo e atterraggio verticale.
Marco Caputo, Anthony Byron Prada Abstract The objective of this thesis is to design a UAV capable of vertical taking off and landing (VTOL) from an aerodynamic point of view. Throughout this thesis a requirement sheet explained step by step how to make the right choices. This resulted in having a design that is possible to build and fly. A VTOL UAV was chosen to be developed mainly due to the purpose of the UAV itself. In fact, it is meant to be a research platform that can be deployed for many different tasks through a removable and customized sensor box. Thus, it will be used by many different people, most of whom have no experience flying a UAV. The solution is to make a completely automatic machine that consents flying for inexperienced people. For this reason, the VTOL configuration comes in handy, it is fairly easy to automate. There are not many UAVs or general aviation aircraft capable of VTOL. The reason is that from an aerodynamic and mechanical point of view it is a very difficult task to achieve. Different concepts where explored and through brainstorming a reference concept was chosen to be developed. The development process comprehends a series of steps that starts with the propulsion system and goes through the wing geometry definition ( span, tapper ratio, geometric twist, root angle etc.), airfoil selection, vertical and horizontal tail geometry definition, and finishes with a stability evaluation that leads to the positioning of the center of mass. Throughout the development many models were made, each of which had its pros and cons. From the first sketch to the final model it is possible to see the evolution of the adjustments and considerations that were made. In the end, the model 5.0c was selected as the final model because it was thought to be satisfying from a theoretical point of view. Before the manufacturing of the full scale model, to validate the theory, the final design was studied with CFD simulations and wind tunnel testing. Most of the CFD simulations were computed in steady state to get a mean value of the lift, drag, and pitching moments. A few were simulated in an unsteady state to see the vortex evolution and the possible oscillations in the forces and moments. Finally, a 3D printed 1:8 scaled model was manufactured to make a wind tunnel test to validate the CFD model. Of course, there is always space for future developments and improvements that were not possible because of time or budget constraints. A brief chapter is dedicated to a discussion of what further improvements could have been made if more time had been available.