한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제46권7호
  • /
  • Pages.542-550
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  • 2018
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  • 1225-1348(pISSN)
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  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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헬리콥터 진동 하중 저감을 위한 능동 뒷전 플랩이 장착된 SNUF 블레이드의 유연보의 설계 및 해석

Design and Analysis of Flexbeam in SNUF Blade Equipped with Active Trailing-Edge Flap for Helicopter Vibratory Load Reduction

  • 투고 : 2018.03.31
  • 심사 : 2018.06.21
  • 발행 : 2018.07.01
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초록

본 논문에서는 헬리콥터의 전진비행시 발생하는 허브 진동 하중 저감을 위해 설계된 능동 뒷전 플랩이 장착된 SNUF 블레이드의 무베어링 주 로터 적용 설계에 대해 살펴보았다. 이를 위해 EDISON의 박벽 복합재료 회전보 진동해석 프로그램(CORBA77_MEMB)을 이용하여 유연보의 단면 설계가 이루어졌다. 다물체 동역학 해석 프로그램 DYMORE를 이용하여 단면 설계에 따른 블레이드 동특성 및 능동 뒷전 플랩을 이용한 하중 제어의 특성을 예측하였다.

This paper presents design of a bearingless main rotor of SNUF (Seoul National University Flap) blade equipped with active trailing-edge flap to reduce the hub vibratory loads during helicopter forward flight. For that purpose, sectional design of the flexbeam is carried out using the thin-walled composite material rotating beam vibration analysis program (CORBA77_MEMB) in EDISON. Using the multi-body dynamics analysis program, DYMORE, blade dynamic characteristics and those of the loads control are examined using the active trailing-edge flap in terms of the flexbeam sectional design.

키워드

참고문헌

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