UAV slat design with wind tunnel verification to support Flight performance tests

Yung Lan Yeh, Chin-E. Lin, Ching Lung Lu

研究成果: Article同行評審

摘要

Slat and flap controls are known to improve flight performance in lift under low speed operation. For Unmanned aerial vehicle (UAV), constraints in design and implementation limit its flight performance in lower speed operation. For many UAV applications, low speed high lift performance is important in various missions. This paper presents a UAV design with slat and flap for high lift at low speed. A wind tunnel model is made to examine the aerodynamic characteristics before fabrication into flight tests. UAV slat design, wind tunnel experiment, polystyrene fabrication, system implementation and flight test are recorded. Based on the UAV redesign, a flight control can be implemented to achieve low speed operations in high performance.

原文English
頁(從 - 到)95-102
頁數8
期刊Journal of Aeronautics, Astronautics and Aviation
48
發行號2
DOIs
出版狀態Published - 2016 六月 1

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

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