ANALISIS KEKUATAN STRUKTUR WING KOMPOSIT SANDWICH
PESAWAT UAV CARGO-X
Total View This Week0
Total View This Week0
Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
HABIBI, HABIBI
Subject
T Technology (General)
Datestamp
2024-07-19 08:26:43
Abstract :
In the process of developing air transportation technology in this era, much must be considered and re-examined by prospective engineering such as in sizzling aircraft, among others, the structure. The Cargo-x UAV aircraft is an aircraft designed as an aircraft to carry medicines, packages and blood bags in areas that require fast and efficient handling. With this goal, of course, cargo-x UAV aircraft must have toughness in all conditions. One of the most important components is wing, in analyzing the structure of the wing, of course must have a lightweight and strong material, among others: composite material that serves to have the advantage of strength and light composite sandwich itself consists of thin skin and thick core that serves to provide protection on the surface of the component. The process of modeling wing using help of Catia V5R21 software, and composite sandwich structure analysis process, using MSC patran/Nastran 2012 software with import stage, meshing, material property input, load and pedestal, analysis process. The results of the analysis will be in the form of the maximum voltage of the wing structure. Furthermore, calculations will be done to know the value of margine of safety in isotropic elements, namely in the core and spar, and failure indices on composite elements namely skin. The maximum voltage result that occurs in the skin structure is 62.5 MPa with failure indeces layer 2 of 0.218, for the core part the maximum voltage that occurs is 1.16 MPa, with a margine of safety -0.447, for the maximum voltage spar part that occurs at 453 MPa with a margine of safety of 1.75, then based on the data tsb UAV cargo-x wing structure is not safe for Core, And safe for skins and spar.
In the process of developing air transportation technology in this era, much must be considered and re-examined by prospective engineering such as in sizzling aircraft, among others, the structure. The Cargo-x UAV aircraft is an aircraft designed as an aircraft to carry medicines, packages and blood bags in areas that require fast and efficient handling. With this goal, of course, cargo-x UAV aircraft must have toughness in all conditions. One of the most important components is wing, in analyzing the structure of the wing, of course must have a lightweight and strong material, among others: composite material that serves to have the advantage of strength and light composite sandwich itself consists of thin skin and thick core that serves to provide protection on the surface of the component. The process of modeling wing using help of Catia V5R21 software, and composite sandwich structure analysis process, using MSC patran/Nastran 2012 software with import stage, meshing, material property input, load and pedestal, analysis process. The results of the analysis will be in the form of the maximum voltage of the wing structure. Furthermore, calculations will be done to know the value of margine of safety in isotropic elements, namely in the core and spar, and failure indices on composite elements namely skin. The maximum voltage result that occurs in the skin structure is 62.5 MPa with failure indeces layer 2 of 0.218, for the core part the maximum voltage that occurs is 1.16 MPa, with a margine of safety -0.447, for the maximum voltage spar part that occurs at 453 MPa with a margine of safety of 1.75, then based on the data tsb UAV cargo-x wing structure is not safe for Core, And safe for skins and spar.
Download
book
BibTex
Latex, Jabref
cloud_download
Original Resource
url resource Institution
