3D YAZICI İLE ÜRETİLEN DÖRT ROTORLU İHA ŞASESİNİN SONLU ELEMANLAR YÖNTEMİ TABANLI YAPISAL ANALİZİ
Küçük Resim Yok
Tarih
2020
Dergi Başlığı
Dergi ISSN
Cilt Başlığı
Yayıncı
Kütahya Dumlupinar University
Erişim Hakkı
info:eu-repo/semantics/openAccess
Özet
Bu çalışmada iniş platformları ile uyumlu dört rotorlu küçük İHA (insansız hava aracı) tasarımının sonlu elemanlar yöntemiyle statik analizi ve imalatı yapılmıştır. Statik analizde, dört rotorlunun kendi ağırlığı yük olarak kabul edilmiş ve tabanı sabitlenmiştir. Sonlu elemanlar analizinde(SEA) kullanılan dört rotorlunun her bir parçası Akrilonitril Bütadien Stiren (ABS) ve Poliaktik Asit (PLA) malzemelerinden i3 Prusa yazıcı ile 0.05 mm katman kalınlığında üretilmiştir. Yapısal analiz sonucunda ABS malzemesinden üretilen dört rotorlu şasesinde oluşan gerilme 0,053 MPa iken, PLA malzemesinden üretilen dört rotorlu şasesinde oluşan gerilme ise 0,065 MPa olarak hesaplanmıştır. Ayrıca, ABS malzemesinden üretilen dört rotorlu şasesinde oluşan deformasyon 0,014 mm iken, PLA malzemesinden üretilen dört rotorlu İHA şasesinde ise 0,010 mm olarak tespit edilmiştir.
In this study, the static analysis and manufacturing of a quadcopter type small unmanned aerial vehicle (UAV) design compatible with landing platforms was performed by using the finite element method. In static analysis, the weight of the quadcopter body is considered as the load and the base is fixed. Each part of the quadcopter used in the Finite Element Analysis (FEA) is manufactured with Acrylonitrile Butadiene Styrene (ABS) and Polyactic Acid (PLA) materials with a thickness of 0.05 mm with i3 prusa printer. As a result of the structural analysis, the stress produced in the quadcopter chassis produced from ABS material was 0,053 MPa and the stress on the quadcopter frame produced from PLA material was calculated as 0,065 MPa. In addition, the deformation in the quadcopter frame produced from ABS material was 0,014 mm, while the quadcopter frame produced from PLA material was 0,010 mm.
In this study, the static analysis and manufacturing of a quadcopter type small unmanned aerial vehicle (UAV) design compatible with landing platforms was performed by using the finite element method. In static analysis, the weight of the quadcopter body is considered as the load and the base is fixed. Each part of the quadcopter used in the Finite Element Analysis (FEA) is manufactured with Acrylonitrile Butadiene Styrene (ABS) and Polyactic Acid (PLA) materials with a thickness of 0.05 mm with i3 prusa printer. As a result of the structural analysis, the stress produced in the quadcopter chassis produced from ABS material was 0,053 MPa and the stress on the quadcopter frame produced from PLA material was calculated as 0,065 MPa. In addition, the deformation in the quadcopter frame produced from ABS material was 0,014 mm, while the quadcopter frame produced from PLA material was 0,010 mm.
Açıklama
2018-067
Anahtar Kelimeler
3 Boyutlu imalat, sonlu elemanlar yöntemi, dört rotorlu insansız hava aracı
