Advances in aircraft and spacecraft science

  • 제4권1호
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  • Pages.65-80
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  • 2017
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  • 2287-528X(pISSN)
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  • 2287-5271(eISSN)
테크노프레스 (Techno-Press)
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Design optimization of a fixed wing aircraft

  • Yayli, Ugur C. (Department of Mechanical Engineering, Karabuk University) ;
  • Kimet, Cihan (Department of Mechanical Engineering, Karabuk University) ;
  • Duru, Anday (Department of Mechanical Engineering, Karabuk University) ;
  • Cetir, Ozgur (Department of Mechanical Engineering, Karabuk University) ;
  • Torun, Ugur (Department of Mechanical Engineering, Karabuk University) ;
  • Aydogan, Ahmet C. (Department of Mechanical Engineering, Karabuk University) ;
  • Padmanaban, Sanjeevikumar (Ohm Technologies, Research and Development) ;
  • Ertas, Ahmet H. (Department of Biomedical Engineering, Karabuk University)
  • 투고 : 2016.06.06
  • 심사 : 2016.09.19
  • 발행 : 2017.01.25
⟨ 이전 논문 다음 논문 ⟩

초록

Small aircrafts, Unmanned Aerial Vehicles (UAVs), are used especially for military purposes. Because landing fields are limited in rural and hilly places, take-off or landing distances are very important. In order to achieve a short landing or take-off distance many parameters have to be considered, for instance the design of aircrafts. Hence this paper represents a better design to enlarge the use of fixed wing aircrafts. The document is based on a live and simulated experiments. The various components of designed aircraft are enhanced to create short take-off distance, greater lift and airflow without the need for proper runway area. Therefore, created aerodynamics of the remotely piloted aircraft made it possible to use fixed wing aircrafts in rural areas.

키워드

과제정보

연구 과제번호 : Karabuk University-Coordinator of Research Projects (BAP)

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