Wing analysis structure of fixed-wing VTOL UAV SA-1.
In: AIP Conference Proceedings, Jg. 3053 (2024-04-21), Heft 1, S. 1-8
Konferenz
Zugriff:
Fixed-wing VTOL SA-1 is a fixed-wing type of UAV that is designed to have vertical take-off capability. This capability is due to the addition of 4 motors on the wings. In this study, the wing structural strength of fixed-wing VTOL SA-1 was calculated using the finite element method. The data obtained from the calculations are the maximum stress, safety factor, and deflection. This research begins by creating an embodiment of the model of the wing structure. The half-wing structure with the load from the driving motor and aerodynamic forces is assumed to be a fixed support type cantilever. In the cruise phase, the maximum deflection is 10.47 mm (at the wing tip), the maximum stress is 17.512 MPa (the wing spar), and the safety factor is 4.0057. From the calculation results of the take-off phase, the maximum deflection value is 15.125 mm (on the motor mounting), the maximum stress is 29.256 MPa (on the wing spar) and the safety factor is 1.569. This calculation shows that the wing structure meets the criteria, so it is safe to fly in the take-off phase or cruise phase. [ABSTRACT FROM AUTHOR]
Titel: |
Wing analysis structure of fixed-wing VTOL UAV SA-1.
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Autor/in / Beteiligte Person: | Fatra, Warman ; Anuar, Kaspul ; Cupu, Dedi Rosa Putra ; Matua, Tambat ; Utama, Ryan Riski |
Zeitschrift: | AIP Conference Proceedings, Jg. 3053 (2024-04-21), Heft 1, S. 1-8 |
Quelle: | 2024, Vol. 3053 Issue 1, p1-8. 8p.; Jg. 3053 (2024-04-21) 1, S. 1-8 |
Veröffentlichung: | 2024 |
Medientyp: | Konferenz |
ISSN: | 0094-243X (print) |
DOI: | 10.1063/5.0199782 |
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