CBL - Campus del Baix Llobregat

Projecte llegit

Títol: eVTOL aircraft concept - Wing and canard study and design

Estudiants que han llegit aquest projecte:

Director/a: MELLIBOVSKY ELSTEIN, FERNANDO PABLO

Departament: FIS

Títol: eVTOL aircraft concept - Wing and canard study and design

Data inici oferta: 11-07-2022     Data finalització oferta: 11-03-2023


Estudis d'assignació del projecte:
    GR ENG SIST AEROESP
Tipus: Individual
 
Lloc de realització: EETAC
 
Paraules clau:
aircraft, ONAerospace, chord, MAC, slope, XFLR5, OpenVSP, Ansys, Solidworks, eVTOL, lift, stall, drag, HLD, CFD, wings, airfoil, flaps, Fowler flap, slats, ailerons, elevator, rudder, Vtail, Wing slant, body, electrical Ducted Fan (eDfan)
 
Descripció del contingut i pla d'activitats:
The aim of this project is to design and assemble all surfaces and
devices intended for lift production of an eVTOL aircraft. All
lift devices combined will provide an optimum lift/drag ratio
during cruise, and sufficient lift and controls for T/O and LAND
phases.

The main focus will be placed on wing and Vtail shape and
dimensions, including both simulation and, if possible, experiment
in wind tunnel.

The work plan will be as follows:

0) Application of conceptual technology to forward the current
(preliminary) design of the wings.
conceptual technology.
1) Optimisation of wing and canard surfaces under ducted-fan lift-
producing conditions in transition phases.
2) Analysis of semi-morphing wings and winglets.
3) Primary and secondary flight control devices.
4) Lift integration study of all external parts of the aircraft
combined.
 
Overview (resum en anglès):
The evolution of urban air mobility is pushing the boundaries of air transportation as we currently know it: in the forthcoming years, the first iterations of personal air vehicles will emerge, making air travel cheaper and more accessible than ever before. One of these projects is ONAerospace, a start-up which intends to develop an electrically-powered aircraft with VTOL capabilities to perform the typical tasks helicopters do. To achieve such goal, several studies for each of the main components of the aircraft have been assigned to be developed in parallel, in order to provide a first assessment on a concept prototype that can be further refined later on. Consequently, this study has focused on the main wing design, with the objective to provide ONAerospace with a viable design that can accomplish the project objectives and requirements.

The design philosophy is centered around simplicity and practicality, in an attempt to guarantee fast and easy alterations to the proposed design if deemed necessary, and to reduce future development and manufacture costs. Moreover, this study nurtures itself from past and present research on the aircraft in an effort to provide continuity to such efforts.

An iterative process has been followed in the design stage, where the airfoil design parameters are set, then tested with CFD analysis, and if the result does not comply with the required performance, the initial parameters are changed. Then the process is repeated again, until an airfoil that satisfies all the aircraft aerodynamic needs is validated. The tools and software used for this process have been XFLR5 and OpenVSP to test airfoil and wing properties, Solidworks for the airfoil design, and Ansys for the validation of its 2D aerodynamic properties. A full 3D CFD analysis remains pending.

The final iteration has resulted in a slightly tapered wing with a mean aerodynamic chord of 1.5 meters and a wingspan of 12 meters. Due to its inability to comply with stall requirements all on its own, a Fowler flap with a chord 30\% that of the airfoil has been implemented. The resulting wing is deemed feasible and longitudinally stable, despite having some parameters still undefined. Nonetheless, the chord is still considered too large to fit safely into the airframe; therefore, some important design decisions will have to be taken in subsequent studies if such wing solution is pushed for implementation.

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