Development, optimisation and manufacturing of novel drones
Fahad, Fahad (2026)
Diplomityö
2026
School of Energy Systems, Konetekniikka
Kaikki oikeudet pidätetään.
Julkaisun pysyvä osoite on
https://urn.fi/URN:NBN:fi-fe2026061672334
https://urn.fi/URN:NBN:fi-fe2026061672334
Tiivistelmä
The research presents the design, structural analysis, and mechanical evaluation of a hybrid VTOL UAV with a deployable wing and a rear-mounted coaxial thrust-vectoring propulsion system. The study focuses specifically on the mechanical and structural performance of the deployable wing mechanism and the thrust vectoring system based on a gimbal during the most demanding transition period between vertical hover and forward flight, accounting for both aerodynamic and actuation loads.
To achieve efficient transition between vertical take-off and forward flight, increase flight endurance and range, reduce power consumption, and maintain a simple, lightweight, easily manufacturable mechanical architecture for 3D-printed hybrid VTOL UAV systems, a biomimetic foldable wing mechanism was designed. A two-axis gimbal mechanism was designed to enable the capability of thrust vectoring for stabilization and transition control. The complete design of the UAV system was created in SolidWorks, and then its structural properties and aerodynamics of different designs were validated by finite element analysis (FEA) and computational fluid dynamics (CFD).
It was determined that the partially deployed wing was the one that was critical for structural integrity, because it had higher stresses on the wing hinge and bending gradients at the wing root from both aerodynamic and mechanical forces. The gimbal was stiffer than required and had a load capacity over the range of operation analyzed, and the selected material was within allowable stresses.
The results show the need for a comprehensive mechanical, structural, and aerodynamic assessment of reconfigurable VTOL UAV systems. The proposed design offers a feasible mechanical structure that will improve the reliability, efficiency, and stability of transitions in hybrid VTOL aircraft.
To achieve efficient transition between vertical take-off and forward flight, increase flight endurance and range, reduce power consumption, and maintain a simple, lightweight, easily manufacturable mechanical architecture for 3D-printed hybrid VTOL UAV systems, a biomimetic foldable wing mechanism was designed. A two-axis gimbal mechanism was designed to enable the capability of thrust vectoring for stabilization and transition control. The complete design of the UAV system was created in SolidWorks, and then its structural properties and aerodynamics of different designs were validated by finite element analysis (FEA) and computational fluid dynamics (CFD).
It was determined that the partially deployed wing was the one that was critical for structural integrity, because it had higher stresses on the wing hinge and bending gradients at the wing root from both aerodynamic and mechanical forces. The gimbal was stiffer than required and had a load capacity over the range of operation analyzed, and the selected material was within allowable stresses.
The results show the need for a comprehensive mechanical, structural, and aerodynamic assessment of reconfigurable VTOL UAV systems. The proposed design offers a feasible mechanical structure that will improve the reliability, efficiency, and stability of transitions in hybrid VTOL aircraft.