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Light Wing Spar Design for High Altitude Long Endurance UAV

고고도 장기체공무인기 경량 주익 스파 설계

  • 신정우 (한국항공우주연구원 항공기술연구소) ;
  • 박상욱 (한국항공우주연구원 항공기술연구소) ;
  • 이무형 (한국항공우주연구원 항공기술연구소) ;
  • 김태욱 (한국항공우주연구원 항공기술연구소)
  • Received : 2014.05.27
  • Accepted : 2014.06.17
  • Published : 2014.06.30

Abstract

There are several methods to improve the flight efficiency of HALE(High Altitude Long Endurance) UAV(Unmaned Aerial Vehicle). Airframe structural point of view, weight reduction of the airframe structure is the most important method to improve the flight efficiency. In order to reduce the weight of airframe structures, new concepts which are different from traditional airframe structure design such as the mylar wing skin should be introduced. The spar is the most important component in a mylar skin wing structure, so the spar weight reduction is the key point for reduction of the wing structural weight. In this study, design trade-off study for the front spar of the HALE UAV wing is conducted in order to reduce the weight. Design and analysis procedure of high aspect ratio wing spar are introduced. Several front spar structures are designed and trade-off study regarding the weight and strength for the each spar are performed. Spar design configurations are verified by the static strength test. Finally, optimal front spar design is decided and applied to the HALE UAV wing design.

Keywords

References

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  3. 단면분할 원통형 복합재료 날개 보 설계 및 해석 vol.47, pp.10, 2014, https://doi.org/10.5139/jksas.2019.47.10.687
  4. 성층권 장기체공 무인기 주익 구조 해석 및 건전성 평가 vol.27, pp.4, 2019, https://doi.org/10.12985/ksaa.2019.27.4.001