CBL - Campus del Baix Llobregat

Projecte llegit

Títol: Main wing and Tail concept design for an eVTOL aircraft prototype

Estudiants que han llegit aquest projecte:

Director/a: MELLIBOVSKY ELSTEIN, FERNANDO PABLO

Departament: FIS

Títol: Main wing and Tail concept design for an eVTOL aircraft prototype

Data inici oferta: 08-02-2022     Data finalització oferta: 08-10-2022


Estudis d'assignació del projecte:
    GR ENG SIST AEROESP
Tipus: Individual
 
Lloc de realització: EETAC
 
Nom del segon director/a (UPC): Jaume Suriaca
Departament 2n director/a:
 
Paraules clau:
VTOL aircraft, Electric propulsion, Concept design, wings, flaps, slats, ailerons, spoilers, stabilizer, elevator, rudder, vtail
 
Descripció del contingut i pla d'activitats:
The aim of this project is to build upon an ongoing project to design and implement the aerodynamic package of the eVtol. This will provide the aircraft with optimum lift/drag efficiency during the cruise phase, and enough lift and manoeuvrability in the T/O and LAND flight phases.

The Project will need to develop the airfoil and wing shapes and the Vtail via CFD simulation, to reach the best wing surface required for the aircraft. The purpose of this work is a realistic technical development for the effective function of the wings inside the aircraft, without forgetting at any time, the design and practicality of the wings, within the total structure of the aircraft.

The work plan will be as follows:

0) Airfoil/Wing preliminary study
1) Analysis of ducted fan installation within the wing structure to enhance lift at T/O and LAND.
2) Morphological wings study.
3) Analysis of primary and secondary flight control surfaces.
4) Wing electrical system (fly-by-wire, lights signals, engines electrical system)
 
Overview (resum en anglès):
During the last years, aircraft concept design has been evolved to produce more ecological prototypes while covering aerotaxi functions, needing in that way, Vertical Landing and Take-Off capabilities. For that reason, and to cover search and rescue and/or medical missions, that the ONAerospace jet has been designed, an aircraft with VTOL capabilities that uses conventional wings to generate lift in cruise phase.

In order to design and define this concept, the job has been divided in different works, being designed here mainly the horizontal tail and the main wing, but also defining some general basic design parameters of the vertical tail.

The design objective of this work is to define a wing-tail solution that has inherent longitudinal static stability while being capable of reducing the stall speed up to 20m/s, which would lead to a much lower energy consumption both on takeoff and landing.

The design of these surfaces has been done by following some different wing design books, defining in first place the wing surface, in second place the wing airfoil and in third place the final wing shape. Once these parameters have been defined, the high-lifting surfaces have been added to the wing.

The results validation and the parameter studies have been done through XFLR5, OPÊNVSP and ANSYS, being the two first adequate in low Reynolds numbers and the third being a CFD (Computational Fluid Dynamics) that allows the design validation in real wind tunnel conditions of the proposed solution.

Finally, a valid and stable design has been presented, accomplishing all the previously defined requirements. However, several design considerations and parameters will have to be reconsidered or refined in subsequent studies in order to maximize the total airplane's performance.

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