SIMULASI KEKUATAN STRUKTUR WING UAV VTOL
SKYBEEJO V1
Total View This Week0
Total View This Week0
Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Gilang Saputra, Alfin
Subject
T Technology (General)
Datestamp
2024-05-06 02:46:58
Abstract :
Utilization of drones includes monitoring urban spatial planning, observing forest areas. Skybeejo is one type of fixed-wing UAV owned by CV Archapada Raya. Fixed-wing UAVs cannot take off and land on narrow runways. Therefore, modifications were made to this aircraft from the previous conventional method of takeoff and landing to VTOL (Vertical Takeoff and Landing). Consequently, changes are required in the type of material and geometry to be used in the wing structure. Thus, this study focuses on simulating the strength of the wing structure using carbon fiber and balsa wood as the primary materials to determine the safety of the structure based on the margin of safety. The results show that the half-span geometry is 1325mm with 14 ribs. The maximum stress occurs during maneuver loading at 22.354 MPa, during negative limit loading at 16.785 MPa, and during VTOL loading at 15.176 MPa. The failure criteria and margin of safety indicate that the structure is safe.
Utilization of drones includes monitoring urban spatial planning, observing forest areas. Skybeejo is one type of fixed-wing UAV owned by CV Archapada Raya. Fixed-wing UAVs cannot take off and land on narrow runways. Therefore, modifications were made to this aircraft from the previous conventional method of takeoff and landing to VTOL (Vertical Takeoff and Landing). Consequently, changes are required in the type of material and geometry to be used in the wing structure. Thus, this study focuses on simulating the strength of the wing structure using carbon fiber and balsa wood as the primary materials to determine the safety of the structure based on the margin of safety. The results show that the half-span geometry is 1325mm with 14 ribs. The maximum stress occurs during maneuver loading at 22.354 MPa, during negative limit loading at 16.785 MPa, and during VTOL loading at 15.176 MPa. The failure criteria and margin of safety indicate that the structure is safe.
Download
book
BibTex
Latex, Jabref
cloud_download
Original Resource
url resource Institution
