ANALISIS KEKUATAN STRUKTUR SAYAP PADA
PESAWAT UAV V-SKY 14 MENGGUNAKAN SOFTWARE
MSC PATRAN/NASTRAN
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
NOVIARATRI LARASATI, ANISA
Subject
T Technology (General)
Datestamp
2024-07-25 02:46:23
Abstract :
UAV (Unmanned Aerial Vehicle) is an aircraft without human pilot onboard that are being developed but need a long runway for take off. However, for a traffic surveillance and aerial surveillance, a long runway might be not available. To answer that, a vertical take off UAV is needed. Wings is an important part to support loads of aircraft, then structure that can withstand all aerodynamic forces as well as stress is needed. Therefore, the researcher did an analysis to find out the biggest stress that happened and the safety of wings structure. Aircraft modelling process used MSC Patran/Nastran software started with geometry import from CATIA software, meshing, properties input, putting load and constrain then analysed. During the loading, there are two conditions applied, when the aircraft did vertical take off and when cruising with 3.8 load factor. After being analyzed and obtained stress value, calculation is done to get margine of safety. The results from analysis founf the value of maximum stress in cruising condition in stringer is 68,4 Mpa with 11,675 margin of safety. The value of margin of safety in wing is 2,816 with stress value of 0,168 MPa and VTOL beam 65,692 with 13 Mpa stress value. While in vertical take off condition, the maximum stress in VTOL beam is 160 MPa with margin of safety value 4,419. For margin of safety wing 1,954 with 0,217 Mpa of stress and stringer margin of safety 21,876 with stress value of 37,9 MPa.
UAV (Unmanned Aerial Vehicle) is an aircraft without human pilot onboard that are being developed but need a long runway for take off. However, for a traffic surveillance and aerial surveillance, a long runway might be not available. To answer that, a vertical take off UAV is needed. Wings is an important part to support loads of aircraft, then structure that can withstand all aerodynamic forces as well as stress is needed. Therefore, the researcher did an analysis to find out the biggest stress that happened and the safety of wings structure. Aircraft modelling process used MSC Patran/Nastran software started with geometry import from CATIA software, meshing, properties input, putting load and constrain then analysed. During the loading, there are two conditions applied, when the aircraft did vertical take off and when cruising with 3.8 load factor. After being analyzed and obtained stress value, calculation is done to get margine of safety. The results from analysis founf the value of maximum stress in cruising condition in stringer is 68,4 Mpa with 11,675 margin of safety. The value of margin of safety in wing is 2,816 with stress value of 0,168 MPa and VTOL beam 65,692 with 13 Mpa stress value. While in vertical take off condition, the maximum stress in VTOL beam is 160 MPa with margin of safety value 4,419. For margin of safety wing 1,954 with 0,217 Mpa of stress and stringer margin of safety 21,876 with stress value of 37,9 MPa.
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