Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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A Validation Study on Structural Load Analyses of TiltRotors in Wind Tunnel

풍동 시험용 틸트로터의 구조 하중 해석의 검증 연구

  • Ui-Jin Hwang (Department of Aerospace Engineering, Chungnam National University ) ;
  • Jae-Sang Park (Department of Aerospace Engineering, Chungnam National University ) ;
  • Myeong-Kyu Lee (UAM Research Division, Korea Aerospace Research Institute)
  • 황의진 (충남대학교 항공우주공학과 ) ;
  • 박재상 (충남대학교 항공우주공학과 ) ;
  • 이명규 (한국항공우주연구원 항공연구소 UAM 연구부)
  • Received : 2022.12.08
  • Accepted : 2023.02.20
  • Published : 2023.04.30
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Abstract

This study conducted aeromechanics modeling and structural load analyses of Tilt Rotor Aeroacoustic Model (TRAM), a 25% scaled V-22 tiltrotor model used in wind tunnel tests. A rotorcraft comprehensive analysis code, CAMRAD II, was used. Analysis results of this study in low-speed forward flights were compared with DNW test and previous analysis results. Blade flap bending moments were in good agreement with measured data. Mean values and oscillatory loads for lead-lag bending and torsion moments were slightly different from measured data. However, when mean values were removed, results of structural loads for one rotor revolution were moderately compared with wind tunnel tests and previous analyses. Total forces and half peak-to-peak forces of the pitch link reasonably well matched with previous analysis results and measured data. Finally, harmonic magnitudes of blade structural loads were investigated.

본 연구에서는 V-22 Osprey 틸트로터의 25% 축소 모델인 TRAM에 대하여 회전익기 통합 해석 코드인 CAMRAD II를 이용하여 프롭로터의 Aeromechanics 모델링과 블레이드 및 피치 링크에 대한 구조 하중 해석을 수행한 후, DNW 풍동 시험 및 선행 해석 연구 결과와 상호 비교하였다. 본 연구에서는 저속 전진 비행 시 블레이드 플랩 굽힘 모멘트의 구조 하중 및 진동 하중 변화를 풍동 시험 결과에 대하여 비교적 잘 예측하였다. 리드-래그 굽힘 및 비틀림 모멘트의 구조 하중 및 진동 하중 해석은 풍동 시험과 다소 다르게 얻어졌으나, 평균값을 제거하였을 때 로터 회전 한 바퀴당 구조 하중 해석 결과가 풍동 시험 및 선행 해석 연구와 비교적 유사하였다. 피치 링크의 구조 하중 및 진동 하중 해석은 전반적으로 선행 연구의 시험 및 해석 결과와 유사하게 얻어졌다. 마지막으로 블레이드 구조 진동 하중의 조화 성분 해석 및 비교를 통하여 블레이드 리드-래그 굽힘 및 비틀림 모멘트의 오차 발생 원인을 분석하였다.

Keywords

Acknowledgement

본 연구는 2020년도 정부(교육부)의 재원으로 한국연구재단의 기초연구사업의 지원을 받아 수행되었습니다(2020R1I1A3071793). 본 논문은 2021년도 정부(과학기술정보통신부)의 재원으로 한국연구재단의 지원을 받아 수행된 연구입니다(2021R1A5A1031868). 본 논문의 일부는 한국항공우주학회 2022년 추계학술대회에서 발표되었습니다.

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