항공우주시스템공학회지 (Journal of Aerospace System Engineering)

  • 제16권6호
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  • Pages.106-113
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  • 2022
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  • 1976-6300(pISSN)
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  • 2508-7150(eISSN)
항공우주시스템공학회 (The Society for Aerospace System Engineering)
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eVTOL 항공기 블레이드 피치 제어용 선형 구동기 기본설계 모델의 구조 안전성 평가

Structural Safety Evaluation of Basic Design Model of Linear Actuator for Blade Pitch Control of eVTOL Aircraft

  • 김영철 (한경대학교 ICT로봇기계공학부) ;
  • 김동협 (한경대학교 융합시스템공학과) ;
  • 김상우 (한경대학교 ICT로봇기계공학부) ;
  • 강정현 ((주)영풍전자) ;
  • 김도형 (한화에어로스페이스(주))
  • Young-Cheol, Kim (School of ICT, Robotics & Mechanical Engineering, Hankyong National University) ;
  • Dong-Hyeop, Kim (Department of Integrated Systems Engineering, Hankyong National University) ;
  • Sang-Woo, Kim (School of ICT, Robotics & Mechanical Engineering, Hankyong National University) ;
  • Jeong-Hyun, Kang (Youngpoong Electronics Co., Ltd.) ;
  • Dohyung, Kim (Hanwha Aerospace Co., Ltd.)
  • 투고 : 2022.08.26
  • 심사 : 2022.10.24
  • 발행 : 2022.12.31
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초록

본 연구에서는 eVTOL 개인항공기의 개별 블레이드 피치 제어용 선형 구동기 기본설계 모델에 대한 구조 안전성을 검토하였다. Stall 하중에 대한 정적 구조 안전성을 검토하기 위해 유한요소법을 이용한 응력해석을 수행하여 안전여유율을 계산하였다. 또한 선형 구동기의 운용조건에 대한 피로수명을 평가하기 위해 피로 해석을 수행하였다. 다물체 동역학 분석을 통해 블레이드 피치각에 따른 하중이력을 산출하였다. 또한 정하중 해석에 정격하중을 적용하여 응력 분포를 산출하고 피로 해석에 활용하였다. 해석 결과, 선형 구동기의 모든 부품은 0 이상의 안전여유율이 계산되었고, 107 cycles 이상의 피로수명이 산출되어 구조적으로 안전함이 확인되었다.

The structural safety of the basic design model of the linear actuator for the individual blade pitch control of eVTOL personal aircraft was investigated. Stress analysis based on the finite element method was conducted, and the margin of safety was calculated to examine the structural safety under stall load conditions. Additionally, fatigue analysis was conducted to evaluate the fatigue life of the linear actuators under operating conditions. The load history with the blade pitch angle was calculated using multi-body dynamics analysis, and the static load analysis was used to obtain the stress distribution for the rated load. As a result, it was confirmed that the safety margins exceeded zero, and the fatigue lives of all linear actuator components exceeded 107 cycles, indicating a safe structural range.

키워드

과제정보

본 논문은 2021년도 정부(산업통신자원부)의 재원으로 한국산업기술평가관리원의 지원을 받아 수행된 연구 결과임(No.20015907, eVTOL 모빌리티용 고신뢰도, 고속, 고출력 다중화 전기식 작동기 개발).

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