한국군사과학기술학회지 (Journal of the Korea Institute of Military Science and Technology)

  • 제24권4호
  • /
  • Pages.357-367
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  • 2021
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  • 1598-9127(pISSN)
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  • 2636-0640(eISSN)
한국군사과학기술학회 (The Korea Institute of Military Science and Technology)
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고속 비행의 Lift-offset 복합형 헬리콥터 기체의 능동 진동 제어 시뮬레이션

Active Airframe Vibration Control Simulations of Lift-offset Compound Helicopters in High-Speed Flights

  • 홍성부 (충남대학교 항공우주공학과) ;
  • 권영민 (한화시스템(주) 기반기술연구소 기계설계팀) ;
  • 김지수 (충남대학교 항공우주공학과) ;
  • 이유빈 (충남대학교 항공우주공학과) ;
  • 박병현 (충남대학교 항공우주공학과) ;
  • 신현철 (충남대학교 항공우주공학과) ;
  • 박재상 (충남대학교 항공우주공학과)
  • Hong, Sung-Boo (Department Aerospace Engineering, Chungnam National University) ;
  • Kwon, Young-Min (Mechanical Design Team, Fundamental Technology Research Center, Hanwha Systems) ;
  • Kim, Ji-Su (Department Aerospace Engineering, Chungnam National University) ;
  • Lee, Yu-Been (Department Aerospace Engineering, Chungnam National University) ;
  • Park, Byeong-Hyeon (Department Aerospace Engineering, Chungnam National University) ;
  • Shin, Hyun-Cheol (Department Aerospace Engineering, Chungnam National University) ;
  • Park, Jae-Sang (Department Aerospace Engineering, Chungnam National University)
  • 투고 : 2021.03.25
  • 심사 : 2021.07.02
  • 발행 : 2021.08.05
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초록

This paper studies the simulations of active airframe vibration controls for the Sikorsky X2 helicopter with a lift-offset coaxial rotor. The 4P hub vibratory loads of the X2TD rotor are obtained from the previous work using a rotorcraft comprehensive analysis code, CAMRAD II. The finite element analysis software, MSC.NASTRAN, is used to model the structural dynamics of the X2TD airframe and to analyze the 4P vibration responses of the airframe. A simulation study using Active Vibration Control System(AVCS) with Fx-LMS algorithm to reduce the airframe vibrations is conducted. The present AVCS is modeled using MATLAB Simulink. When AVCS is applied to the X2TD airframe at 250 knots, the 4P longitudinal and vertical vibration responses at the specified airframe positions, such as the pilot seat, co-pilot seat, engine deck, and prop gearbox, are reduced by 30.65 ~ 94.12 %.

키워드

과제정보

본 연구는 국방과학연구소의 지원으로 차세대 고속 복합형 무인 회전익기 특화연구실에서 수행되었습니다. 본 논문의 일부는 한국항공우주학회 2021년도 춘계학술대회에서 발표되었습니다.

참고문헌

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